27020 Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 

required by paragraphs (g), (h), and (i) and of 

this AD. 

(r) 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. 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. 

(s) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2010– 

0081, dated April 27, 2010, and the service 

information specified in paragraphs (s)(1)(i) 

through (s)(1)(xix) of this AD, for related 

information. 

(i) Airbus All Operators Telex (AOT) 

A330–27A3129, Revision 01, dated July 16, 

2004. 

(ii) Airbus Mandatory Service Bulletin 

A330–27–3136, Revision 01, dated July 19, 

2006. 

(iii) Airbus Mandatory Service Bulletin 

A330–27–3146, Revision 01, dated 

September 3, 2008. 

(iv) Airbus Mandatory Service Bulletin 

A330–27–3148, Revision 01, dated October 9, 

2008. 

(v) Airbus Mandatory Service Bulletin 

A330–27–3176, Revision 02, dated April 24, 

2012. 

(vi) Airbus Mandatory Service Bulletin 

A330–27–3177, dated December 21, 2011. 

(vii) Airbus Mandatory Service Bulletin 

A330–27A3131, Revision 01, dated March 3, 

2005. 

(viii) Airbus Mandatory Service Bulletin 

A340–27–4144, dated October 19, 2009. 

(ix) Airbus Mandatory Service Bulletin 

A340–27–4146, dated June 1, 2007. 

(x) Airbus Mandatory Service Bulletin 

A340–27–4148, dated June 13, 2008. 

(xi) Airbus Mandatory Service Bulletin 

A340–27–4162, Revision 01, dated 

September 17, 2012. 

(xii) Airbus Mandatory Service Bulletin 

A340–27–4174, dated November 21, 2011. 

(xiii) Airbus Mandatory Service Bulletin 

A340–27A4130, Revision 01, dated March 3, 

2005. 

(xiv) Airbus Service Bulletin A330–27– 

3134, Revision 01, dated May 12, 2006. 

(xv) Airbus Service Bulletin A330–27– 

3144, Revision 01, dated July 16, 2009. 

(xvi) Airbus Service Bulletin A330–27– 

3145, dated December 16, 2008. 

(xvii) Airbus Service Bulletin A340–27– 

4145, dated December 16, 2008. 

(xviii) Airbus Temporary Revision TR4, 

Issue 1.0, ‘‘TR 4.02.00/25 Issue 2— 

Undetected Elevator Control Loss in Case of 

Dual Failure,’’ dated November 26, 2009, to 

the Airbus A330/A340 Airplane Flight 

Manual. 

(xix) Airbus Temporary Revision TR22, 

Issue 1.0, ‘‘TR 4.02.00/40 Issue 2— 

Undetected Elevator Control Loss in Case of 

Dual Failure,’’ dated November 26, 2009, to 

the Airbus A330/A340 Airplane Flight 

Manual. 

(2) For service information identified in 

this 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, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(t) 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 (AOT) 

A330–27A3129, Revision 01, dated July 16, 

2004. 

(ii) Airbus Mandatory Service Bulletin 

A330–27–3136, Revision 01, dated July 19, 

2006. 

(iii) Airbus Mandatory Service Bulletin 

A330–27–3146, Revision 01, dated 

September 3, 2008. 

(iv) Airbus Mandatory Service Bulletin 

A330–27–3148, Revision 01, dated October 9, 

2008. 

(v) Airbus Mandatory Service Bulletin 

A330–27–3176, Revision 02, dated April 24, 

2012. 

(vi) Airbus Mandatory Service Bulletin 

A330–27–3177, dated December 21, 2011. 

(vii) Airbus Mandatory Service Bulletin 

A330–27A3131, Revision 01, dated March 3, 

2005. 

(viii) Airbus Mandatory Service Bulletin 

A340–27–4144, dated October 19, 2009. 

(ix) Airbus Mandatory Service Bulletin 

A340–27–4146, dated June 1, 2007. 

(x) Airbus Mandatory Service Bulletin 

A340–27–4148, dated June 13, 2008. 

(xi) Airbus Mandatory Service Bulletin 

A340–27–4162, Revision 01, dated 

September 17, 2012. 

(xii) Airbus Mandatory Service Bulletin 

A340–27–4174, dated November 21, 2011. 

(xiii) Airbus Mandatory Service Bulletin 

A340–27A4130, Revision 01, dated March 3, 

2005. 

(xiv) Airbus Service Bulletin A330–27– 

3134, Revision 01, dated May 12, 2006. 

(xv) Airbus Service Bulletin A330–27– 

3144, Revision 01, dated July 16, 2009. 

(xvi) Airbus Service Bulletin A330–27– 

3145, dated December 16, 2008. 

(xvii) Airbus Service Bulletin A340–27– 

4145, dated December 16, 2008. 

(xviii) Airbus Temporary Revision TR4, 

Issue 1.0, ‘‘TR 4.02.00/25 Issue 2— 

Undetected Elevator Control Loss in Case of 

Dual Failure,’’ dated November 26, 2009, to 

the Airbus A330/A340 Airplane Flight 

Manual. 

(xix) Airbus Temporary Revision TR22, 

Issue 1.0, ‘‘TR 4.02.00/40 Issue 2— 

Undetected Elevator Control Loss in Case of 

Dual Failure,’’ dated November 26, 2009, to 

the Airbus A330/A340 Airplane Flight 

Manual. 

(3) For service information identified in 

this 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. 

(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 February 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10653 Filed 5–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1316; Directorate 

Identifier 2012–NM–186–AD; Amendment 

39–17429; AD 2012–18–13 R1] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for all The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 


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Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 27021 

airplanes. That AD currently requires 

repetitive inspections to detect cracking 

in the web of the aft pressure bulkhead 

at body station 1016 at the aft fastener 

row attachment to the ‘‘Y’’ chord, 

various inspections for discrepancies at 

the aft pressure bulkhead, and related 

investigative and corrective actions if 

necessary. This new AD requires 

clarifying certain actions specified in 

the existing AD. This AD was prompted 

by several reports of fatigue cracks in 

the aft pressure bulkhead. We are 

issuing this AD to detect and correct 

such fatigue cracking, which could 

result in rapid decompression of the 

fuselage. 

DATES: This AD is effective June 13, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 24, 2012 (77 FR 57990, 

September 19, 2012). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 10, 1999 (64 FR 

19879, April 23, 1999). 

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 

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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6450; fax: (425) 917–6590; email: 

alan.pohl@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). That AD applies to 

all The Boeing Company Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes. (AD 2012–18–13 

superseded AD 99–08–23, Amendment 

39–11132 (64 FR 19879, April 23, 

1999)). The NPRM published in the 

Federal Register on January 9, 2013 (78 

FR 1772). That NPRM proposed to 

continue to require repetitive 

inspections to detect cracking in the 

web of the aft pressure bulkhead at body 

station 1016 at the aft fastener row 

attachment to the ‘‘Y’’ chord, various 

inspections for discrepancies at the aft 

pressure bulkhead, and related 

investigative and corrective actions if 

necessary. That NPRM also proposed to 

clarify certain actions specified in the 

existing AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 1772, 

January 9, 2013) and the FAA’s response 

to each comment. 

Supportive Comment 

The Boeing Company stated that it 

supports the NPRM (78 FR 1772, 

January 9, 2013). 

Supplemental Type Certificate (STC) 

Comment 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2c6e3dbddd36f91c8625

76a4005d64e2/$FILE/ST01219SE.pdf) 

does not affect the accomplishment of 

the manufacturer’s service instructions. 

We have added paragraph (c)(2) of 

this AD to state that installation of STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2c6e3dbddd36f91c862576a

4005d64e2/$FILE/ST01219SE.pdf) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST01219SE 

is installed, a ‘‘change in product’’ 

AMOC approval request is not necessary 

to comply with the requirements of 14 

CFR 39.17. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change 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 1772, 

January 9, 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 1772, 

January 9, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 566 

airplanes of U.S. registry. 

ESTIMATED COSTS

Action Labor cost Parts 

cost Cost per product Cost on U.S. operators 

Low frequency eddy current 

(LFEC) inspection [retained action from AD 99–08–23, Amendment 39–11132 (64 FR 19879, 

April 23, 1999)].

8 work-hours × $85 per hour = $680 ............... $0 $680 ............................ $384,880. 

Detailed visual inspection [retained 

action from AD 99-08–23, 

Amendment 39–11132 (64 FR 

19879, April 23, 1999)].

2 work-hours × $85 per hour = $170 ............... 0 $170 ............................ $96,220. 


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27022 Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 

ESTIMATED COSTS—Continued 

Action Labor cost Parts 

cost Cost per product Cost on U.S. operators 

Detailed, high frequency eddy current (HFEC), and LFEC inspections of the web at the ‘‘Y’’ chord 

of the bulkhead, the web located 

under the outer circumferential 

tear strap, the ‘‘Z’’ stiffeners at 

the dome cap, and existing repairs [retained actions from AD 

2012–18–13, Amendment 39– 

17190 (77 FR 57990, September 

19, 2012)].

Up to 60 work-hours × $85 per hour = $5,100 

per inspection cycle.

0 Up to $5,100 per inspection cycle.Up to $2,886,600 per 

inspection cycle. 

We estimate the following costs to do 

any necessary on-condition inspections 

that would be required based on the 

results of the initial inspection. We have 

no way of determining the number of 

aircraft that might need these 

inspections: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Detailed and HFEC inspections for oil-canning ................ 1 work-hour × $85 per hour = $85 .................................. $0 $85 

LFEC or HFEC inspection for cracking ............................ 2 work-hours × $85 per hour = $170 ............................... 0 170 

We have received no definitive data 

that would enable us to provide cost 

estimates for the crack repairs specified 

in this AD. 

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 have 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 

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 

removing airworthiness directive (AD) 

2012–18–13, Amendment 39–17190 (77 

FR 57990, September 19, 2012), and 

adding the following new AD: 

2012–18–13 R1 The Boeing Company: 

Amendment 39–17429; Docket No. 

FAA–2012–1316; Directorate Identifier 

2012–NM–186–AD. 

(a) Effective Date 

This AD is effective June 13, 2013. 

(b) Affected ADs 

This AD revises AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http:// 

rgl.faa.gov/ 

Regulatory_and_Guidance_Library/rgstc.nsf/ 

0/2c6e3dbddd36f91c862576a4005d64e2/ 

$FILE/ST01219SE.pdf) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST01219SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by several reports 

of fatigue cracks in the aft pressure bulkhead. 

We are issuing this AD to detect and correct 


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Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 27023 

such fatigue cracking, which could result in 

rapid decompression of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial Inspection 

This paragraph restates the initial 

inspection required by paragraph (g) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). Perform either 

inspection specified by paragraph (g)(1) or 

(g)(2) of this AD at the time specified in 

paragraph (h) of this AD. 

(1) Perform a low frequency eddy current 

(LFEC) inspection from the aft side of the aft 

pressure bulkhead to detect discrepancies 

(including cracking, misdrilled fastener 

holes, and corrosion) of the web of the upper 

section of the aft pressure bulkhead at body 

station 1016 at the aft fastener row 

attachment to the ‘‘Y’’ chord, from stringer 15 

left (S–15L) to stringer 15 right (S–15R), in 

accordance with Boeing 737 Nondestructive 

Test Manual D6–37239, Part 6, Section 53– 

10–54, dated December 5, 1998. 

(2) Perform a detailed visual inspection of 

the aft fastener row attachment to the ‘‘Y’’ 

chord from the forward side of the aft 

pressure bulkhead to detect discrepancies 

(including cracking, misdrilled fastener 

holes, and corrosion) of the entire web of the 

aft pressure bulkhead at body station 1016. 

(h) Retained Compliance Times 

This paragraph restates the compliance 

times specified in paragraph (h) of AD 2012– 

18–13, Amendment 39–17190 (77 FR 57990, 

September 19, 2012). Perform the inspection 

required by paragraph (g) of this AD at the 

time specified in paragraph (h)(1), (h)(2), or 

(h)(3) of this AD, as applicable. 

(1) For airplanes that have accumulated 

40,000 or more total flight cycles as of May 

10, 1999 (the effective date of AD 99–08–23, 

Amendment 39–11132 (64 FR 19879, April 

23, 1999)): Inspect within 375 flight cycles or 

60 days after May 10, 1999 (the effective date 

of AD 99–08–23), whichever occurs later. 

(2) For airplanes that have accumulated 

25,000 or more total flight cycles and fewer 

than 40,000 total flight cycles as of May 10, 

1999 (the effective date of AD 99–08–23, 

Amendment 39–11132 (64 FR 19879, April 

23, 1999)): Inspect within 750 flight cycles or 

90 days after May 10, 1999 (the effective date 

of AD 99–08–23), whichever occurs later. 

(3) For airplanes that have accumulated 

fewer than 25,000 total flight cycles as of 

May 10, 1999 (the effective date of AD 99– 

08–23, Amendment 39–11132 (64 FR 19879, 

April 23, 1999)): Inspect prior to the 

accumulation of 25,750 total flight cycles. 

(i) Retained Repetitive Inspections 

This paragraph restates the repetitive 

inspections required by paragraph (i) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). Within 1,200 

flight cycles after performing the initial 

inspection required by paragraph (g) of this 

AD, and thereafter at intervals not to exceed 

1,200 flight cycles: Perform either inspection 

specified by paragraph (g)(1) or (g)(2) of this 

AD. 

(j) Retained Corrective Actions 

This paragraph restates the corrective 

actions required by paragraph (j) of AD 2012– 

18–13, Amendment 39–17190 (77 FR 57990, 

September 19, 2012). If any discrepancy is 

detected during any inspection required by 

paragraph (g), (h), or (i) of this AD: Prior to 

further flight, accomplish the actions 

specified by paragraphs (j)(1) and (j)(3) of this 

AD, and paragraph (j)(2) of this AD, if 

applicable. 

(1) Perform a high frequency eddy current 

inspection from the forward side of the 

bulkhead to detect cracking of the web at the 

‘‘Y’’ chord attachment, around the entire 

periphery of the ‘‘Y’’ chord, in accordance 

with Boeing 737 Nondestructive Test Manual 

D6–37239, Part 6, Section 51–00–00, Figure 

23, dated November 5, 1995. 

(2) If the most recent inspection performed 

in accordance with paragraph (g) of this AD 

was not a detailed visual inspection: 

Accomplish the actions specified by 

paragraph (g)(2) of this AD. If the inspection 

was a detailed visual inspection, it is not 

necessary to repeat that inspection prior to 

further flight. 

(3) Repair any discrepancy such as 

cracking or corrosion or misdrilled fastener 

holes using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(k) Retained Inspections of the Web at the 

‘‘Y’’ Chord Upper Bulkhead From 

S–15L to S–15R 

This paragraph restates the inspections of 

the web at the ‘‘Y’’ chord upper bulkhead 

from S–15L to S–15R required by paragraph 

(k) of AD 2012–18–13, Amendment 39–17190 

(77 FR 57990, September 19, 2012). At the 

later of the times specified in paragraphs 

(k)(1) and (k)(2) of this AD: Do detailed and 

LFEC inspections of the aft side of the 

bulkhead web, or do detailed and high 

frequency eddy current (HFEC) inspections 

from the forward side of the bulkhead, and 

do all applicable related investigative and 

corrective actions; in accordance with Part 1 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, except 

as required by paragraphs (r)(1) and (r)(3) of 

this AD. Inspect for cracks, incorrectly 

drilled fastener holes, and elongated fastener 

holes. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspections at the applicable 

times specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. 

(1) Prior to the accumulation of 25,000 

total flight cycles. 

(2) Except as required by paragraphs (r)(2) 

and (r)(4) of this AD, at the later of the times 

specified in the ‘‘Compliance Time’’ column 

in table 1 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011. 

(l) Retained Inspections of the Web at the 

‘‘Y’’ Chord in the Lower Bulkhead From S– 

15L to S–15R With Revised Inspection and 

Repair Conditions 

This paragraph restates the inspections of 

the web at the ‘‘Y’’ chord in the lower 

bulkhead from S–15L to S–15R required by 

paragraph (l) of AD 2012–18–13, Amendment 

39–17190 (77 FR 57990, September 19, 2012), 

with revised inspection and repair 

conditions. Except as required by paragraphs 

(r)(2) and (r)(5) of this AD, at the applicable 

time specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011: Do detailed and eddy 

current inspections of the web from the 

forward or aft side of the bulkhead for cracks, 

incorrectly drilled fastener holes, and 

elongated fastener holes, in accordance with 

Part III of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011, except as required by paragraphs (r)(1) 

and (r)(3) of this AD. If any crack, incorrectly 

drilled fastener hole, elongated fastener hole, 

or corrosion is found, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. Repeat the 

inspections at the applicable times specified 

in table 2 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011. 

(m) Retained One-Time Inspection Under the 

Tear Strap 

This paragraph restates the one-time 

inspection under the tear strap required by 

paragraph (m) of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). Except as required by 

paragraphs (r)(2) and (r)(5) of this AD, at the 

applicable time specified in table 3 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011: Do a 

one-time LFEC inspection for cracks on the 

aft side of the bulkhead of the web located 

under the outer circumferential tear strap, or 

do a one-time HFEC inspection for cracks 

from the forward side of the bulkhead of the 

web located under the outer circumferential 

tear strap, in accordance with Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011, except as required 

by paragraph (r)(1) of this AD. If any cracking 

is found, before further flight, repair the 

bulkhead using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(n) Retained Inspection for Oil-Canning 

This paragraph restates the inspection for 

oil-canning required by paragraph (n) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). Except as 

required by paragraph (r)(2) of this AD, at the 

applicable time specified in table 4 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011: Do a 

detailed inspection from the aft side of the 

bulkhead for oil-canning and do all 


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applicable related investigative and 

corrective actions, in accordance with Part II 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, except 

as required by paragraph (r)(1) of this AD. Do 

all related investigative and corrective 

actions before further flight. Thereafter, 

repeat the inspection at the applicable times 

specified in table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. For oil-cans found 

within the limits specified in Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011: In lieu of installing 

the repair before further flight, at the 

applicable times specified in table 4 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, do 

initial and repetitive detailed and HFEC 

inspections for cracks of the oil-canning and 

install the repair, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011. If any crack is 

found, before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. Installing the repair 

terminates the repetitive inspections for 

cracks. 

(o) Retained Inspection of the Dome Cap at 

the Center of the Bulkhead 

This paragraph restates the inspection of 

the dome cap at the center of the bulkhead 

required by paragraph (o) of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). Except as required by 

paragraphs (r)(2) and (r)(5) of this AD, at the 

applicable time specified in table 5 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011: Do an 

eddy current inspection to detect any 

cracking of the dome cap at the center of the 

bulkhead, and do all applicable corrective 

actions, in accordance with Part IV of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011. Do all corrective 

actions before further flight. Repeat the 

inspection at the times specified in table 5 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011. 

(p) Retained Inspection of the Forward 

Flange of the ‘‘Z’’ Stiffeners at the Dome Cap 

This paragraph restates the inspection of 

the forward flange of the ‘‘Z’’ stiffeners at the 

dome cap required by paragraph (p) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). Except as 

required by paragraphs (r)(2) and (r)(5) of this 

AD, at the applicable time specified in table 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011: Do an 

HFEC inspection to detect any cracking of the 

‘‘Z’’ stiffener flanges at the dome cap in the 

center of the bulkhead, in accordance with 

Part V of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, except 

as required by paragraph (r)(1) of this AD. If 

any crack is found, before further flight, 

repair the flanges using a method approved 

in accordance with the procedures specified 

in paragraph (u) of this AD. Repeat the 

inspection at the applicable times specified 

in table 6 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011. 

(q) Retained Inspection for Existing Repairs 

on the Bulkhead 

This paragraph restates the inspection for 

existing repairs on the bulkhead required by 

paragraph (q) of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). Except as required by 

paragraph (r)(2) of this AD, at the applicable 

time specified in table 7 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011: Do a detailed inspection 

of the bulkhead web and stiffeners for 

existing repairs, in accordance with Part VI 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, except 

as required by paragraph (r)(1) of this AD. 

(1) If any repair identified in the 

‘‘Condition’’ column of table 8 of paragraph 

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

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, is found and the 

‘‘Reference’’ column refers to Appendix A, B, 

C, or D of that service bulletin: At the 

applicable times specified in table 8 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, except 

as required by paragraph (r)(2) of this AD, do 

an HFEC inspection or an LFEC inspection of 

the web for cracking, in accordance with 

Appendix A, B, C, or D, as applicable, of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011. If any 

cracking is found, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (u) of 

this AD. Repeat the inspections thereafter at 

the applicable intervals specified in table 8 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011. 

(2) If any repair identified in the 

‘‘Condition’’ column of table 8 of paragraph 

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

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, is found and the 

‘‘Reference’’ column refers to Appendix E of 

that service bulletin: At the applicable times 

specified in table 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, except as required by 

paragraph (r)(2) of this AD, remove the repair 

and replace with a new repair, in accordance 

with Appendix E of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. 

(3) If any non-SRM (structural repair 

manual) repair is found and the repair does 

not have FAA-approved damage tolerance 

inspections: Except as required by paragraph 

(r)(2) of this AD, at the applicable time 

specified in table 7 of Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, contact the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

Aircraft Certification Office (ACO), for 

damage tolerance inspections. Do those 

damage tolerance inspections at the times 

given using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(r) Retained Exceptions to the Service 

Information 

This paragraph restates the exceptions to 

the service information required by 

paragraph (r) of AD 2012–18–13, Amendment 

39–17190 (77 FR 57990, September 19, 2012). 

(1) Where Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(2) Where Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011, specifies a compliance time ‘‘after 

the date of Revision 1 to this service 

bulletin,’’ ‘‘from the date of Revision 3 of this 

service bulletin,’’ ‘‘after the date of Revision 

3 to this service bulletin,’’ or ‘‘of the effective 

date of AD 99–08–23,’’ this AD requires 

compliance within the specified compliance 

time after October 24, 2012 (the effective date 

of AD 2012–18–13, Amendment 39–17190 

(77 FR 57990, September 19, 2012)). 

(3) Access and restoration procedures 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011, are not required by this AD. 

Operators may do those procedures following 

their maintenance practices. 

(4) Where table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, specifies a compliance 

time relative to actions done ‘‘in accordance 

with paragraph (a)(2) of AD 99–08–23,’’ this 

AD requires compliance within the specified 

compliance time relative to actions specified 

in paragraph (g)(2) of this AD. 

(5) Where the Condition columns in tables 

2, 3, 5, and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, refer to total flight cycles, 

this AD applies to the airplanes with the 

specified total flight cycles as of October 24, 

2012 (the effective date of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012)). 

(s) Retained Terminating Action With 

Revised Paragraph Reference 

This paragraph restates the terminating 

action specified in paragraph (s) of AD 2012– 

18–13, Amendment 39–17190 (77 FR 57990, 

September 19, 2012), with a revised 

paragraph reference. Accomplishment of the 

requirements in paragraph (k) of this AD 

terminates the requirements of paragraphs (g) 

through (j) of this AD. 


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Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 27025 

(t) Credit for Previous Actions 

This paragraph restates the credit for 

previous actions specified by paragraph (t) of 

AD 2012–18–13, Amendment 39–17190 (77 

FR 57990, September 19, 2012). This 

paragraph provides credit for the actions 

required by paragraphs (k) through (s) of this 

AD, if the actions were performed before the 

effective date of this AD using the service 

bulletins specified in paragraphs (t)(1) 

through (t)(4) of this AD. 

(1) Boeing Alert Service Bulletin 737– 

53A1214, dated June 17, 1999. 

(2) Boeing Alert Service Bulletin 737– 

53A1214, Revision 1, dated June 22, 2000. 

(3) Boeing Alert Service Bulletin 737– 

53A1214, Revision 2, dated May 24, 2001. 

(4) Boeing Alert Service Bulletin 737– 

53A1214, Revision 3, dated January 19, 2011. 

(u) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 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 99–08–23, Amendment 

39–11132 (64 FR 19879, April 23, 1999), are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(v) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: (425) 917–6440; fax: (425) 917– 

6590; email: alan.pohl@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, 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. 

(w) 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 October 24, 2012 (77 FR 

57990, September 19, 2012). 

(i) Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 10, 1999 (64 FR 

19879, April 23, 1999). 

(i) Boeing 737 Nondestructive Test Manual 

D6–37239, Part 6, Section 53–10–54, dated 

December 5, 1998. 

(ii) Boeing 737 Nondestructive Test 

Manual D6–37239, Part 6, Section 51–00–00, 

Figure 23, dated November 5, 1995. 

(5) For Boeing 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. 

(6) 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. 

(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 April 5, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–09113 Filed 5–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0662; Airspace 

Docket No. 08–AWA–2] 

RIN 2120–AA66 

Modification of Class B Airspace; 

Philadelphia, PA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies the 

Philadelphia, PA, Class B airspace area 

to ensure the containment of large 

turbine-powered aircraft within Class B 

airspace, reduce controller workload, 

and reduce the potential for midair 

collision in the Philadelphia terminal 

area. 

DATES: Effective Date: 0901 UTC, July 

25, 2013. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: Paul 

Gallant, Airspace Policy and ATC 

Procedures Group, Office of Airspace 

Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

The FAA published in the Federal 

Register a notice of proposed 

rulemaking (NPRM) to modify the 

Philadelphia, PA, Class B airspace area 

(77 FR 45290, July 31, 2012). Interested 

parties were invited to participate in 

this rulemaking effort by submitting 

written comments on the proposal. 

Three comments were received in 

response to the NPRM. The FAA 

considered all comments received 

before making a determination on this 

final rule. 

Discussion of Comments 

All three commenters expressed 

concern over the effect of expanding the 

PHL Class B to the east and southeast. 

One commenter was concerned by the 

possible effect on a busy VFR flyway, 

and by the funnel effect of having only 

1000 feet vertically between the 

modified Class B and Alert Area A–220. 

Another commenter was concerned that 

more complicated airspace, combined 

with a bad economy and the high cost 

of flight training, would discourage 


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