28240 Federal Register / Vol. 77, No. 93 / Monday, May 14, 2012 / Rules and Regulations 

contains the NPRM (76 FR 61641, 

October 5, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–09–07 Airbus: Amendment 39–17042. 

Docket No. FAA–2011–0998; Directorate 

Identifier 2011–NM–046–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 18, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A319– 

111, –112, and –132 airplanes; Model A320– 

111, –211, –212, –214 and –232 airplanes; 

and Model A321–111, –211, –212, and –231 

airplanes; certificated in any category; having 

manufacturer serial numbers 0039, 0078, 

0109, 0118, 0120, 0153, 0174, 0187, 0203, 

0215, 0218, 0226, 0227, 0228, 0236, 0237, 

0269, 0270, 0278, 0285, 0286, 0287, 0288, 

0294, 0301, 0337, 0377, 0462, 0463, 0464, 

0465, 0520, 0523, 0528, 0876, 0888, 0921, 

0935, 0974, 1014, 1102, 1130, 1160, 1162, 

1177, 1215, 1250, 1287, 1336, 1388, 1404, 

1444, 1449, 1476, 1505, 1524, 1564, 1605, 

1616, 1622, 1640, 1645, 1658, 1677, 1691, 

1729, and 1905. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports that 

corrosion was found on the overwing 

refueling aperture on the top wing skin, and 

that for certain airplanes, repairs made using 

primer coating may prevent proper electrical 

bonding provision between the overwing 

refueling cap adaptor and the wing skin. We 

are issuing this AD to detect and correct 

corrosion and improper bonding, which in 

combination with a lightning strike in this 

area, could create a source of ignition in a 

fuel tank, resulting in a fire or explosion, and 

consequent loss 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) Electrical Bonding Test and General 

Visual Inspection if Necessary 

Within 24 months after the effective date 

of this AD, do an electrical bonding test to 

check for bonding between the re-fuel 

adaptor of the gravity fill and the top skin 

panels on the left-hand and right-hand wings, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, dated June 14, 2010. 

(1) If the resistance value is 10 milliOhms 

or less at the left-hand and right-hand wing, 

no further action is required. 

(2) If the resistance value is greater than 10 

milliOhms at the left-hand or right-hand 

wing, before further flight, do a general visual 

inspection for corrosion of the component 

interface and adjacent area, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010. If any corrosion is found 

during the inspection, before further flight, 

repair the gravity fill fuel adaptor, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, dated June 14, 2010; except where 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010, specifies to contact 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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, Washington 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. 

(i) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0034, dated March 2, 2011; 

and Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010; for related information. 

(j) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 30, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–11027 Filed 5–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0993; Directorate 

Identifier 2011–NM–018–AD; Amendment 

39–17043; AD 2012–09–08] 

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 767–200 

and –300 series airplanes. This AD was 


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prompted by reports of multiple site 

damage cracks in the radial web lap and 

tear strap splices of the aft pressure 

bulkhead at station (STA) 1582 due to 

fatigue. This AD requires repetitive 

inspections for cracking of the aft 

pressure bulkhead at STA 1582, repair 

or replacement of any cracked bulkhead, 

and eventual replacement of the aft 

pressure bulkhead at STA 1582 with a 

new bulkhead. Accomplishing the 

replacement terminates the repetitive 

inspections required by this AD. We are 

issuing this AD to prevent fatigue 

cracking of the aft pressure bulkhead, 

which could result in rapid 

decompression of the airplane and 

possible damage or interference with the 

airplane control systems that penetrate 

the bulkhead, and consequent loss of 

controllability of the airplane. 

DATES: This AD is effective June 18, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 18, 2012. 

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; email 

me.boecom@boeing.com; 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone (425) 

917–6577; fax (425) 917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on September 27, 2011 (76 FR 

59590). That NPRM proposed to require 

repetitive inspections for cracking of the 

aft pressure bulkhead at station (STA) 

1582, repair or replacement of any 

cracked bulkhead, and eventual 

replacement of the aft pressure 

bulkhead at STA 1582 with a new 

bulkhead. That proposed AD specified 

that accomplishing the replacement 

would terminate the repetitive 

inspections specified in the NPRM. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for NPRM (76 FR 59590, 

September 27, 2011) 

American Airlines has no objection to 

the NRPM (76 FR 59590, September 27, 

2011), and noted that it will incorporate 

the requirements into its maintenance 

program. 

Request To Include AD 2004–14–19, 

Amendment 39–13728 (69 FR 42549, 

July 16, 2004) in NPRM (76 FR 59590, 

September 27, 2011) Requirements 

Boeing and Airborne Express (ABX) 

asked that the requirements in AD 

2004–14–19, Amendment 39–13728 (69 

FR 42549, July 16, 2004), be added to 

the affected ADs section and the related 

requirements of the NPRM (76 FR 

59590, September 27, 2011). Boeing 

stated that this would ensure that the 

initial actions in paragraphs (b), (c), and 

(d) of AD 2004–14–19 begin 50,000 

flight cycles after the aft pressure 

bulkhead has been replaced. ABX 

recommend that we add a paragraph 

that allows a 50,000 flight cycle 

threshold on a new aft pressure 

bulkhead for the inspections required by 

AD 2004–14–19. 

We do not agree to include AD 2004– 

14–19, Amendment 39–13728 (69 FR 

42549, July 16, 2004), in the affected 

ADs section and related requirements of 

this AD. We have determined that an 

unsafe condition exists, and that the 

actions this AD requires are adequate to 

ensure the continued safety of the 

affected fleet. The commenter’s 

suggested changes would alter the 

actions currently required by this AD, so 

additional rulemaking would be 

required. We find that delaying this 

action would be inappropriate in light 

of the identified unsafe condition. We 

have not changed this final rule 

regarding this issue. However, operators 

can always request approval of an 

alternative method of compliance 

(AMOC) for AD 2004–14–19. 

Request To Clarify Terminating Action 

for Other ADs 

Boeing asked that we change 

paragraph (g) of the NPRM (76 FR 

59590, September 27, 2011) to remove 

the terminating action for the repetitive 

inspections specified in paragraph (b) of 

AD 2004–05–16, Amendment 39–13511 

(69 FR 10917, March 9, 2004). Boeing 

stated that the inspections required by 

paragraph (b) of AD 2004–05–16 are not 

terminated by doing the inspections 

required by paragraph (g) of the NPRM. 

Boeing added that the inspections 

required by AD 2004–05–16 are for 

cracking of the web of the aft pressure 

bulkhead at the web y-chord joint. 

Boeing noted that this cracking pattern, 

location, and growth rate are not 

covered by the inspection in paragraph 

(g) of the NPRM. 

We agree with the commenter for the 

reasons provided. We have removed the 

terminating action for the repetitive 

inspections required by AD 2004–05–16 

(69 FR 10917, March 9, 2004) from 

paragraph (g) of this AD. 

Boeing also requested that we revise 

paragraph (g) of the NPRM (76 FR 

59590, September 27, 2011) to specify 

that accomplishing the inspections in 

paragraph (g) of the NPRM terminates 

the ‘‘initial’’ and repetitive inspections 

required by paragraphs (f) ‘‘and (h)’’ of 

AD 2005–03–11, Amendment 39–13967 

(70 FR 7174, February 11, 2005), 

corrected on March 11, 2005 (70 FR 

12119). 

We partially agree with the 

commenter. Doing the inspections 

required by paragraph (g) of this AD 

replaces the inspections (repetitive) 

required by paragraph (f) of AD 2005– 

03–11, Amendment 39–13967 (70 FR 

7174, February 11, 2005), corrected on 

March 11, 2005 (70 FR 12119). We have 

revised paragraph (g) of this AD 

accordingly. However, the inspection 

required by paragraph (h) of AD 2005– 

03–11 is a one-time inspection of the 

‘‘oil can’’ locations of the aft pressure 

bulkhead web, which is not in the same 

location as the inspections required by 

paragraph (g) of the NPRM (76 FR 

59590, September 27, 2011). Therefore 

the requirements in paragraph (h) of AD 

2005–03–11 cannot be terminated by the 

inspections required by paragraph (g) of 


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this AD. However, under the provisions 

of paragraph (i) of this AD, we will 

consider requests to provide such relief 

through approval of an AMOC if 

sufficient data are submitted to 

substantiate that the terminating action 

would also provide an acceptable level 

of safety. 

Boeing also asked that we revise 

paragraph (h) of the NPRM (76 FR 

59590, September 27, 2011) to specify 

that doing the replacement specified in 

paragraph (h) of the NPRM terminates 

the actions required by paragraphs (a) 

and (b) of AD 2004–05–16, Amendment 

39–13511 (69 FR 10917, March 9, 2004) 

and the actions required by paragraphs 

(f) and (h) of AD 2005–03–11, 

Amendment 39–13967 (70 FR 7174, 

February 11, 2005), corrected on March 

11, 2005 (70 FR 12119). 

We agree with the commenter. Once 

the replacement required by paragraph 

(h) of this AD is done, it is not necessary 

to do the inspections required by 

paragraphs (a) and (b) of AD 2004–05– 

16, Amendment 39–13511 (69 FR 

10917, March 9, 2004) and paragraphs 

(f) and (h) of AD 2005–03–11, 

Amendment 39–13967 (70 FR 7174, 

February 11, 2005), corrected on March 

11, 2005 (70 FR 12119). We have revised 

paragraph (h) of this AD accordingly. 

Request To Include Inspection in 

Airworthiness Limitations 

ABX asked that we add a new 

paragraph following paragraph (h) of the 

NPRM (76 FR 59590, September 27, 

2011), which allows synchronizing the 

maintenance program and the AD 

requirements for all airplanes equipped 

with improved aft pressure bulkheads. 

ABX added that we should mandate the 

airworthiness limitations (AWLs) for the 

maintenance on aft pressure bulkheads 

that have been replaced, in order to 

relieve the burden of requesting 

AMOCs. ABX added that the improved 

aft pressure bulkhead should have the 

same maintenance requirements 

whether it was installed on an airplane 

in production or in service. 

We partially agree with the 

commenter. We agree that the actual 

dimensional and material configuration 

of the modified aft pressure bulkhead is 

identical to the later production 

airplanes. However, although the 

configuration is identical, the fatigue 

life of the bulkhead is not. All Model 

767 airplanes, including the fatigue test 

airplanes, are subject to limit test 

pressurization loads during production. 

This limit loading substantially 

enhances the fatigue life of the 

structure. We have made no change to 

the AD in this regard. 

Clarification of Effect of Winglet 

Installation 

We have added new Note 1 to 

paragraph (c) of this AD to state that 

supplemental type certificate (STC) 

ST01920SE (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgstc.nsf/0/082838ee177dbf62862576a

4005cdfc0/$FILE/ST01920SE.pdf) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST01920SE 

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 changes described previously. 

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 83 

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 

Inspections .............................. 22 work-hours × $85 per hour = $1,870 per inspection cycle $0 $1,870 $155,210 

Replacement ........................... 1,541 work-hours × $85 per hour = $130,985 ....................... 399,539 530,524 44,033,492 

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): 

2012–09–08 The Boeing Company: 

Amendment 39–17043; Docket No. 


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Federal Register / Vol. 77, No. 93 / Monday, May 14, 2012 / Rules and Regulations 28243 

FAA–2011–0993; Directorate Identifier 

2011–NM–018–AD. 

(a) Effective Date 

This AD is effective June 18, 2012. 

(b) Affected ADs 

Certain requirements of this AD affect 

certain requirements of AD 2004–05–16, 

Amendment 39–13511 (69 FR 10917, March 

9, 2004), and AD 2005–03–11, Amendment 

39–13967 (70 FR 7174, February 11, 2005), 

corrected on March 11, 2005 (70 FR 12119). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200 and –300 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 767–53A0139, 

dated November 12, 2009. 

Note 1 to paragraph (c) of this AD: 

Supplemental Type Certificate (STC) 

ST01920SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/082838ee177dbf62862576a4005cdfc0/

$FILE/ST01920SE.pdf) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST01920SE 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 reports of 

multiple site damage cracks in the radial web 

lap and tear strap splices of the aft pressure 

bulkhead at station (STA) 1582 due to 

fatigue. We are issuing this AD to prevent 

fatigue cracking of the aft pressure bulkhead, 

which could result in rapid decompression of 

the airplane and possible damage or 

interference with the airplane control 

systems that penetrate the bulkhead, and 

consequent loss of controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as provided by paragraph (h) of this 

AD: Before the accumulation of 43,000 total 

flight cycles, or within 1,600 flight cycles 

after the effective date of this AD, whichever 

occurs later, do detailed, low-frequency eddy 

current, and mid-frequency eddy current 

inspections for cracking of the aft pressure 

bulkhead at STA 1582, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 767–53A0139, dated 

November 12, 2009. If any crack is found, 

before further flight, replace the bulkhead as 

required by paragraph (h) of this AD, or 

repair the crack in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0139, dated 

November 12, 2009, and repeat the 

inspections thereafter at intervals not to 

exceed 1,600 flight cycles. If no crack is 

found, repeat the inspections thereafter at 

intervals not to exceed 1,600 flight cycles. 

Accomplishing the inspections required by 

this paragraph terminates the inspections 

required by paragraph (f) of AD 2005–03–11, 

Amendment 39–13967 (70 FR 7174, February 

11, 2005), corrected on March 11, 2005 (70 

FR 12119). 

(h) Replacement 

Except as provided by paragraph (g) of this 

AD: Before the accumulation of 43,000 total 

flight cycles, or within 5,000 flight cycles 

after the effective date of this AD, whichever 

occurs later: Replace the aft pressure 

bulkhead at STA 1582 with a new bulkhead, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0139, dated November 12, 2009. 

Accomplishing the replacement in this 

paragraph terminates the repetitive 

inspections required by paragraph (g) of this 

AD. Accomplishing the replacement in this 

paragraph also terminates the inspections 

required by paragraphs (a) and (b) of AD 

2004–05–16, Amendment 39–13511 (69 FR 

10917, March 9, 2004), and paragraphs (f) 

and (h) of AD 2005–03–11, Amendment 39– 

13967 (70 FR 7174, February 11, 2005), 

corrected on March 11, 2005 (70 FR 12119). 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(j) Related Information 

For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone (425) 917–6577; fax (425) 917– 

6590; email: berhane.alazar@faa.gov. 

(k) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(i) Boeing Alert Service Bulletin 767– 

53A0139, dated November 12, 2009. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356. For information on the availability of 

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

(4) You may also review copies of the 

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/ibr-locations.html. 

Issued in Renton, Washington, on April 29, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–11029 Filed 5–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0099; Airspace 

Docket No. 12–ASO–11] 

Amendment of Class D Airspace; 

Cocoa Beach, FL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; technical 

amendment, correction. 

SUMMARY: This action corrects an error 

in the legal description of a final rule; 

technical amendment, published in the 

Federal Register on April 11, 2012 that 

amends Class D airspace at Cocoa 

Beach, FL. 

DATES: Effective 0901 UTC, May 31, 

2012. The Director of the Federal 

Register approves this incorporation by 

reference action under title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

FOR FURTHER INFORMATION CONTACT: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 


emcdonald on DSK29S0YB1PROD with RULES