Federal Register / Vol. 77, No. 59 / Tuesday, March 27, 2012 / Proposed Rules 18137 

of this AD, or the inspection specified in 

paragraph (g)(1) of this AD, is done. 

(i) If the fuel access panel is found cracked 

during any inspection required by this AD: 

Before further flight, replace the fuel access 

panel with a new fuel access panel having P/ 

N 85714231–003, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011. 

(ii) Within 6,000 flight hours after the 

initial inspection required by paragraph (g)(2) 

of this AD, do the actions required in 

paragraph (g)(1) of this AD, unless the 

replacement required by paragraph (g)(2)(i) of 

this AD is done. 

(h) Inspection and Replacement of P/N 

85714232–001 

Within 1,200 flight hours after the effective 

date of this AD, do an external detailed 

inspection of the outer wing access panels 

having P/N 85714232–001 to locate the rivets 

of the identification plates, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–57–23, 

Revision B, dated February 16, 2011. If the 

rivets of the identification plate are found: 

No further action is required by this 

paragraph for that fuel access panel. If the 

rivets of the identification plate cannot be 

found: Before further flight, do the actions in 

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

(1) Remove fuel access panels having P/N 

85714232–001 and inspect the panels to 

determine if the identification plate is 

installed, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011. If the identification plate 

is found: No further action is required by 

paragraph (h) of this AD for that fuel access 

panel. 

(i) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the access panel does not 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011: No further action is 

required by paragraph (h) of this AD for that 

fuel access panel. 

(ii) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the fuel access panel does 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011: Before further flight, 

replace the fuel access panel with a new fuel 

access panel having P/N 85714232–003, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–23, Revision B, dated February 16, 

2011. 

(2) Do an external detailed inspection on 

fuel access panels having P/N 85714232–001 

for cracking, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011. If no cracking is found: 

Repeat the inspection thereafter at intervals 

not to exceed 1,200 flight hours until the 

replacement specified in paragraph (h)(2)(i) 

of this AD, or the inspection specified by 

paragraph (h)(1) of this AD is done. 

(i) If the fuel access panel is found cracked 

during any inspection required by this AD: 

Before further flight, replace the fuel access 

panel with a new fuel access panel having 

P/N 85714232–003, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011. 

(ii) Within 12,000 flight hours after the 

initial inspection required by paragraph 

(h)(2) of this AD, do the actions required by 

paragraph (h)(1) of this AD, unless the 

replacement required by paragraph (h)(2)(i) 

of this AD is done. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install a fuel access panel having 

P/N 85714231–001 and a job detail number 

listed in table 1 of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–22, Revision B, dated February 16, 

2011; or having P/N 85714232–001 and a job 

detail number listed in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011; on any airplane. 

(j) Credit for Previous Actions 

This paragraph provides credit for 

inspections and fuel access panel 

replacements required by this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 84–57–22, Revision A, dated 

December 9, 2010; or Bombardier Service 

Bulletin 84–57–23, Revision A, dated 

December 9, 2010. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 ACO, send it to Attn: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2011–04, dated March 8, 2011, 

and the following service information, for 

related information. 

(1) Bombardier Service Bulletin 84–57–22, 

Revision B, dated February 16, 2011. 

(2) Bombardier Service Bulletin 84–57–23, 

Revision B, dated February 16, 2011. 

Issued in Renton, Washington on March 

16, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7357 Filed 3–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0299; Directorate 

Identifier 2011–NM–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Boeing Model 747–100, 747–200B, 747– 

200C, 747–200F, 747–300, 747–400, 

747–400F, and 747SR series airplanes. 

This proposed AD was prompted by 

reports of broken and damaged latch pin 

retention bolts of the main deck side 

cargo door (MDSCD), latch pin 

migration, and broken latch pin fittings. 

This proposed AD would require 

various repetitive inspections of the 

MDSCD latch pin fittings, measuring the 

latch pin, and related investigative and 

corrective actions if necessary; and 

modifying the latch pin fittings and 

installing new latch pins and latch pin 

fasteners. We are proposing this AD to 

prevent loss of the cargo door and rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 11, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

18138 Federal Register / Vol. 77, No. 59 / Tuesday, March 27, 2012 / Proposed Rules 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; phone: 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6432; fax: 

425–917–6590; email: Bill.Ashforth@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0299; Directorate Identifier 2011– 

NM–029–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received damage reports on 

MDSCD latch pin fittings. Six operators 

have reported that broken latch pin 

retention bolts were found on eight 

airplanes. On one airplane that had 

accumulated 101,609 total flight hours 

and 12,862 total flight cycles, the 

retention bolts on both the #9 and #10 

latch pin fittings were broken. Latch pin 

#10 had migrated aft and was not 

engaging the latch cam. On another 

airplane that had accumulated 33,983 

total flight hours and 4,723 total flight 

cycles, the retention bolt on the #10 

latch pin fitting was broken and the #9 

latch pin was damaged. On another 

airplane that had accumulated 67,188 

total flight hours and 14,440 total flight 

cycles, the retention bolt for the #10 

latch pin fitting was completely 

sheared, which allowed the latch pin to 

migrate aft until it no longer engaged the 

door latch cam. On four airplanes, only 

the retention bolt on the #10 latch pin 

fitting was found to be broken. On one 

airplane, the retention bolt on the #10 

latch pin fitting was damaged. A loose, 

broken, or missing retention bolt can 

result in a migrated latch pin, which can 

become disengaged from the cargo door 

latch cams and lead to increased loads 

in the adjacent latch pin fittings and 

latch cams. Increased loads can cause 

damage to the cargo door latch 

mechanism and/or the lower sill 

structure. The migration of two or more 

latch pins and subsequent failure of the 

latch mechanism or lower sill structure 

can result in the inability of the cargo 

door to carry limit loads. This 

condition, if not corrected, could result 

in the loss of the cargo door and rapid 

depressurization of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–52A2294, Revision 1, 

dated August 16, 2011, as revised by 

Boeing Alert Service Bulletin 747– 

52A2294, Revision 2, dated December 

12, 2011. For information on the 

procedures and compliance times, see 

this service information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2012–0299. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

repetitive detailed inspections of the 10 

MDSCD latch pin fittings to detect 

loose, broken, missing, or damaged 

retention bolts and nuts; measuring 

latch pin diameter; and related 

investigative and corrective actions, if 

necessary. The related investigative 

actions include a torque check of the 

latch pin retention bolt to determine if 

the bolt is broken; and checking the 

latch pin for migration and, if necessary, 

a detailed inspection for damage of the 

latch pin fitting and the adjacent 

(forward and aft) latch pin fittings, the 

door cutout structure, the affected latch 

cam and the adjacent latch cams, and 

the door structure. The corrective 

actions include replacing the latch pin, 

the retention bolt, and related parts with 

a new latch pin, retention bolt, and 

related parts; and repairing of any 

damage to the adjacent door, door 

cutout structure, and latch cams. 

This proposed AD would also require 

modifying the MDSCD latch pin fittings, 

replacing the latch pins with new latch 

pins, and replacing the latch pin 

retention fasteners with new latch pin 

retention fasteners. In addition, this 

proposed AD would require postmodification/replacement repetitive 

detailed inspections of the MDSCD latch 

pin fittings to detect damaged latch 

pins, and loose, broken, or missing 

retention bolts and nuts; measuring the 

latch pin diameter; and related 

investigative and corrective actions if 

necessary. The related investigative 

actions include checking the latch pin 

for migration and, if necessary, a 

detailed inspection for damage of the 

latch pin fitting and the adjacent latch 

pin fittings, the door cutout structure, 

the affected latch cam and the adjacent 

latch cams on the door, and the door 

structure. The corrective actions include 

replacing the latch pin, the retention 

bolt, and related parts with a new latch 

pin, retention bolt, and related parts; or 

repairing any damage. 

Differences Between the Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 747– 

52A2294, Revision 1, dated August 16, 

2011. as revised by Boeing Alert Service 

Bulletin 747–52A2294, Revision 2, 

dated December 12, 2011, specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

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Federal Register / Vol. 77, No. 59 / Tuesday, March 27, 2012 / Proposed Rules 18139 

Costs of Compliance 

We estimate that this proposed AD 

will affect 77 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Detailed inspection, including 

torque check.

4 work-hours × $85 per hour 

= $340 per inspection cycle.

$0 $340 per inspection cycle ...... $26,180 per inspection cycle. 

Modification ............................ 11 work-hours × $85 per hour 

= $935.

$5,530 $6,465 .................................... $497,805. 

Post-modification detailed inspection.2 work-hours × $85 per hour 

= $170 per inspection cycle.

$0 $170 per inspection cycle ...... $13,090 per inspection cycle. 

We estimate the following costs to do 

necessary repairs and replacements that 

would be required based on the results 

of the proposed inspection. We have no 

way of determining the number of 

aircraft that might need these repairs. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair/Replacements (Groups 1 and 2 airplanes) ...... 7 work-hours × $85 per hour = $595 ........................... $11,478 $12,073 

Repair/Replacements (Group 3 airplanes) ................... 7 work-hours × $85 per hour = $595 ........................... 12,254 12,849 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2012–0299; Directorate Identifier 2011– 

NM–029–AD. 

(a) Comments Due Date 

We must receive comments by May 11, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–200B, 747–200C, 747– 

200F, 747–300, 747–400, 747–400F, and 

747SR series airplanes; certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 747–52A2294, Revision 1, 

dated August 16, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by reports of 

broken and damaged latch pin retention bolts 

of the main deck side cargo door (MDSCD), 

latch pin migration, and broken latch pin 

fittings. We are issuing this AD to prevent 

loss of the cargo door and rapid 

depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

At the applicable compliance time 

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

Boeing Alert Service Bulletin 747–52A2294, 

Revision 1, dated August 16, 2011, as revised 

by Boeing Alert Service Bulletin 747– 

52A2294, Revision 2, dated December 

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18140 Federal Register / Vol. 77, No. 59 / Tuesday, March 27, 2012 / Proposed Rules 

12, 2011, except as provided by paragraph 

(j)(2) of this AD: Do a detailed inspection of 

the 10 MDSCD latch pin fittings to detect 

loose, broken, damaged, or missing retention 

bolts and nuts; measure the latch pin 

diameter; and do all applicable related 

investigative and corrective actions, except as 

required by paragraph (j)(1) of this AD; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–52A2294, Revision 1, dated August 16, 

2011, as revised by Boeing Alert Service 

Bulletin 747–52A2294, Revision 2, dated 

December 12, 2011. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at intervals not to exceed those 

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

Boeing Alert Service Bulletin 747–52A2294, 

Revision 1, dated August 16, 2011, as revised 

by Boeing Alert Service Bulletin 747– 

52A2294, Revision 2, dated December 12, 

2011. 

(h) Modification of Latch Pin Fittings and 

Replacement of Latch Pins and Latch Pin 

Retention Fasteners 

At the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–52A2294, Revision 1, dated 

August 16, 2011, as revised by Boeing Alert 

Service Bulletin 747–52A2294, Revision 2, 

dated December 12, 2011, except as provided 

by paragraph (j)(2) of this AD: Modify the 10 

MDSCD latch pin fittings, replace the latch 

pins with new latch pins, and replace the 

latch pin retention fasteners with new latch 

pin retention fasteners, except as required by 

paragraph (j)(1) of this AD, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–52A2294, 

Revision 1, dated August 16, 2011, as revised 

by Boeing Alert Service Bulletin 747– 

52A2294, Revision 2, dated December 12, 

2011. Accomplishment of the actions in 

paragraph (h) of this AD terminates the 

inspection required in paragraph (g) of this 

AD. 

(i) Post-Modification Inspection and 

Corrective Action 

At the applicable compliance time 

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

Boeing Alert Service Bulletin 747–52A2294, 

Revision 1, dated August 16, 2011, as revised 

by Boeing Alert Service Bulletin 747– 

52A2294, Revision 2, dated December 12, 

2011, except as provided by paragraph (j)(2) 

of this AD: Do a detailed inspection of the 

10 MDSCD latch pin fittings to detect loose, 

broken, damaged, or missing retention bolts 

and nuts; measure the latch pin diameter; 

and do all applicable related investigative 

and corrective actions, except as required by 

paragraph (j)(1) of this AD; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–52A2294, 

Revision 1, dated August 16, 2011, as revised 

by Boeing Alert Service Bulletin 747– 

52A2294, Revision 2, dated December 12, 

2011. Do the applicable related investigative 

and corrective actions before further flight. 

Repeat the inspection thereafter at intervals 

not to exceed those specified in paragraph 

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

Bulletin 747–52A2294, Revision 1, dated 

August 16, 2011, as revised by Boeing Alert 

Service Bulletin 747–52A2294, Revision 2, 

dated December 12, 2011. 

(j) Exceptions to Service Bulletin 

Specifications 

(1) If any damage is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–52A2294, 

Revision 1, dated August 16, 2011, as revised 

by Boeing Alert Service Bulletin 747– 

52A2294, Revision 2, dated December 12, 

2011, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–52A2294, Revision 1, dated August 16, 

2011, as revised by Boeing Alert Service 

Bulletin 747–52A2294, Revision 2, dated 

December 12, 2011, specifies a compliance 

time relative to the issue date of that service 

bulletin, this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–52A2294, dated July 8, 

2010. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, 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 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6432; fax: 425– 

917–6590; email: Bill.Ashforth@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; phone: 

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

5680; email: me.boecom@boeing.com; 

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

You may also review the referenced service 

information in the docket at 

www.regulations.gov (refer to Docket No. 

FAA–2012–0299). You may review copies of 

the referenced service information at the 

FAA, Transport Airplane Directorate, the 

FAA, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on March 

19, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7283 Filed 3–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

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