Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules 72855 

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 

removing airworthiness directive (AD) 

2008–19–03, Amendment 39–15670 (73 

FR 56958, October 1, 2008), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2011–1254; Directorate Identifier 2010– 

NM–178–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by January 12, 2012. 

Affected ADs 

(b) This AD supersedes AD 2008–19–03, 

Amendment 39–15670 (73 FR 56958, October 

1, 2008). 

Applicability 

(c) This AD applies to Model 737–300, 

–400, and –500 series airplanes, certificated 

in any category; as identified in Boeing 

Service Bulletin 737–53A1293, Revision 2, 

dated August 10, 2011. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 53, Fuselage. 

Unsafe Condition 

(e) This AD was prompted by reports of 

additional crack findings of the fuselage skin 

at the chem-mill steps. We are issuing this 

AD to detect and correct fatigue cracking of 

the fuselage skin panels at the chem-mill 

steps, which could result in sudden fracture 

and failure of the fuselage skin panels, and 

consequent rapid decompression of the 

airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections 

(g) At the applicable times specified in 

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

Service Bulletin 737–53A1293, Revision 2, 

dated August 10, 2011, except as provided by 

paragraph (j) and (k) of this AD: Do both a 

detailed inspection and a nondestructive 

inspection (NDI) (medium frequency eddy 

current, magneto optical imaging, C-scan, or 

ultrasonic phased array) to detect cracks in 

the fuselage skin along the chem-mill steps 

at stringers S–1 and S–2R, between station 

(STA) 400 and STA 460, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 737–53A1293, Revision 2, 

dated August 10, 2011. Repeat the applicable 

inspections thereafter at intervals not to 

exceed those specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53A1293, Revision 2, dated August 10, 

2011. 

Repair 

(h) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–53A1293, 

Revision 2, dated August 10, 2011; except as 

provided by paragraph (i) of this AD. 

Installation of a repair that meets the 

conditions specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53A1293, Revision 2, dated August 10, 

2011, terminates the repetitive inspections 

required by paragraph (g) of this AD for the 

repaired area only. 

(i) If any crack is found during any 

inspection required by paragraph (g) of this 

AD and Boeing Service Bulletin 737– 

53A1293, Revision 2, dated August 10, 2011, 

specifies to contact Boeing for repair: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. 

Exceptions to Service Bulletin 

(j) Where Boeing Service Bulletin 737– 

53A1293, Revision 2, dated August 10, 2011, 

specifies a compliance time relative to the 

date on that service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(k) Where the Condition column of 

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

Service Bulletin 737–53A1293, Revision 2, 

dated August 10, 2011, specifies a condition 

based on whether an airplane has or has not 

been inspected, this AD bases the condition 

on whether an airplane has or has not been 

inspected as of the effective date of this AD. 

(l) The post-repair inspection specified in 

Tables 4 and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53A1293, Revision 2, August 10, 2011, 

is not required by this AD. 

Note 1: The damage tolerance inspections 

specified in Tables 4 and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53A1293, Revision 2, August 10, 2011, 

may be used in support of compliance with 

section 121.1109(c)(2) or 129.109(c)(2) of the 

Federal Aviation Regulations (14 CFR 

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

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 737–53A1293, Revision 1, 

July 7, 2010, are acceptable for compliance 

with the corresponding actions required by 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(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. 

(4) AMOCs approved for AD 2008–19–03, 

Amendment 39–15670 (73 FR 56958, October 

1, 2008), are approved as AMOCs for the 

corresponding requirements in this AD. 

Related Information 

(o) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

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

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

(p) 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; 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. 

Issued in Renton, Washington, on 

November 16, 2011. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–30559 Filed 11–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1251; Directorate 

Identifier 2011–NM–017–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


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72856 Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 190 airplanes. 

This proposed AD results from 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as: 

It has been found the occurrence of damage 

on the rod end of the Main Landing Gear 

(MLG) retraction actuator. The ANAC 

[Ageˆncia Nacional de Aviac ̧a ̃o Civil] is 

issuing this AD to prevent breakage of the 

MLG retracting actuator rod, which may 

result in MLG extension with no hydraulic 

damping and consequent damage to the 

locking mechanism and collapse of the MLG. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by January 12, 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER), Technical Publications 

Section (PC 060), Av. Brigadeiro Faria 

Lima, 2170–Putim–12227–901 Sa ̃o Jose 

dos Campos–SP–BRASIL; telephone +55 

12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email 

distrib@embraer.com.br; Internet http:// 

www.flyembraer.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 Operations office 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2768; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–1251; Directorate Identifier 

2011–NM–017–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 based on 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 

The Agencia Nacional De Aviacao 

Civil—Brazil (ANAC), which is the 

airworthiness authority for Brazil, has 

issued Brazilian Airworthiness Directive 

2011–02–01, dated February 12, 2011 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

It has been found the occurrence of damage 

on the rod end of the Main Landing Gear 

(MLG) retraction actuator. The ANAC 

[Ageˆncia Nacional de Aviac ̧a ̃o Civil] is 

issuing this AD to prevent breakage of the 

MLG retracting actuator rod, which may 

result in MLG extension with no hydraulic 

damping and consequent damage to the 

locking mechanism and collapse of the MLG. 

* * * * * 

Required actions include performing a 

one-time general visual inspection to 

determine if a certain part number is 

installed on the left-hand and righthand MLG retraction actuator, and if 

necessary, performing a general visual 

inspection for discrepancies (such as 

cracks, damage, and movement) 

between the actuator rod end and shock 

strut lug of the MLG retraction actuator. 

The corrective action includes, if any 

discrepancy is found during any 

inspection, including any movement 

between the actuator rod-end and shock 

strut lug, replacing the MLG retraction 

actuator, and as applicable the antirotation pin and the attachment bolt 

with a new pin and bolt; and replacing 

the actuator with new actuator having a 

certain part number, and modifying the 

attachment points. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

EMBRAER has issued Service Bulletin 

190–32–0036, dated October 4, 2010; 

and Service Bulletin 190–32–0037, 

dated October 6, 2010. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 73 products of U.S. registry. 


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We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$6,205, or $85 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and require parts 

costing $0, for a cost of $510 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. We have no way of 

determining the number of products 

that may need these actions. 

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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER): Docket No. FAA–2011– 

1251; Directorate Identifier 2011–NM– 

017–AD. 

Comments Due Date 

(a) We must receive comments by January 

12, 2012. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Empresa Brasileira 

de Aeronautica S.A. (EMBRAER) Model ERJ 

190–100 STD, –100 LR, –100 ECJ, and –100 

IGW airplanes; and Model ERJ 190–200 STD, 

–200 LR, and –200 IGW airplanes; 

certificated in any category; all serial 

numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

It has been found the occurrence of damage 

on the rod end of the Main Landing Gear 

(MLG) retraction actuator. The ANAC 

[Ageˆncia Nacional de Aviac ̧a ̃o Civil] is 

issuing this AD to prevent breakage of the 

MLG retracting actuator rod, which may 

result in MLG extension with no hydraulic 

damping and consequent damage to the 

locking mechanism and collapse of the MLG. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 30 days after the effective date 

of this AD, do a one-time general visual 

inspection to determine if part number (P/N) 

190–70980–403 is installed on the left-hand 

and right-hand MLG retraction actuator. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number of the MLG retraction actuator 

can be conclusively determined from that 

review. 

Note 1: For the purpose of this AD, a 

general visual inspection (GVI) is: ‘‘A visual 

examination of an interior or exterior area, 

installation or assembly to detect obvious 

damage, failure or irregularity. This level of 

inspection is made from within touching 

distance, unless otherwise specified. A 

mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight or droplight, and may require 

removal or opening of access panels or doors. 

Stands, ladders or platforms may be required 

to gain proximity to the area being checked.’’ 

(1) No further action is required by 

paragraph (g) of this AD if no MLG retraction 

actuator having P/N 190–70980–403 is found. 

(2) If any MLG retraction actuator having 

P/N 190–70980–403 is found, do a GVI of the 

actuator and bolt (P/N 2821–0028) for 

discrepancies (such as cracks, damage, and 

movement between the actuator rod end and 

shock strut lug of the MLG retraction 

actuator), in accordance with ‘‘Part I’’ of the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 190–32–0036, dated October 

4, 2010, within the applicable compliance 

time specified in paragraphs (g)(2)(i) and 

(g)(2)(ii) of this AD. Repeat the inspection, 

thereafter, at intervals not to exceed 3,500 

flight cycles, until the actions required by 

paragraph (j) of this AD are done. 

(i) For any MLG retraction actuator that has 

accumulated fewer than 3,500 total flight 

cycles as of the effective date of this AD, do 

the GVI of the actuator before the 

accumulation of 4,500 total flight cycles on 

the MLG retraction actuator. 

(ii) For any MLG retraction actuator that 

has accumulated 3,500 total flight cycles or 

more as of the effective date of this AD, do 

the GVI of the actuator within 1,000 flight 

cycles after the effective date of this AD. 

(h) If any discrepancy is found during any 

inspection required by paragraph (g)(2) of 

this AD, including any movement between 

the actuator rod-end and shock strut lug, 

before further flight, replace the MLG 

retraction actuator, and as applicable the 

anti-rotation pin and the attachment bolt, in 

accordance with ‘‘Part II’’ and ‘‘Part III,’’ as 

applicable, of EMBRAER Service Bulletin 

190–32–0036, dated October 4, 2010; except 

where EMBRAER Service Bulletin 190–32– 

0036, dated October 4, 2010, specifies to 

contact the manufacturer, before further 

flight repair in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or Ageˆncia Nacional de 

Aviac ̧a ̃o Civil (or its delegated agent). 

(i) Before any MLG retraction actuator 

having P/N 190–70980–403 accumulates 


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12,000 total flight cycles or within 1,000 

flight cycles after the effective date of this 

AD, whichever occurs later, replace the 

actuator with a new actuator having P/N 

190–70980–405, and modify the attachment 

points, in accordance with ‘‘Part I’’ and ‘‘Part 

II,’’ as applicable, of the Accomplishment 

Instructions of EMBRAER Service Bulletin 

190–32–0037, dated October 6, 2010. 

(j) For all actuators: Within 20,000 flight 

cycles or within 96 months after the effective 

date of this AD, whichever occurs first, do 

the replacement and modification, as 

applicable, in accordance with ‘‘Part III’’ of 

EMBRAER Service Bulletin 190–32–0037, 

dated October 6, 2010. Doing the actions in 

this paragraph is a terminating action for the 

requirements specified in paragraphs (g), (h), 

and (i) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Brazilian Airworthiness Directive 2011–02– 

01, dated February 12, 2011, requires 

replacing the MLG retraction actuator, and as 

applicable, the anti-rotation pin and 

attachment bolt within the next 500 flight 

cycles if any discrepancy is found. However, 

if any discrepancy is found, this AD requires 

replacing the MLG retraction actuator, and as 

applicable, the anti-rotation pin and 

attachment bolt, before further flight. 

Other FAA AD Provisions 

(k) 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: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2768; 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. 

Related Information 

(l) Refer to MCAI Brazilian Airworthiness 

Directive 2011–02–01, dated February 12, 

2011; EMBRAER Service Bulletin 190–32– 

0036, dated October 4, 2010; and EMBRAER 

Service Bulletin 190–32–0037, dated October 

6, 2010; for related information. 

Issued in Renton, Washington, on 

November 10, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–30571 Filed 11–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1255; Directorate 

Identifier 2010–NM–182–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede two 

existing airworthiness directives (AD) 

that apply to Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. The first existing AD 

currently requires, for certain airplanes, 

repetitive inspections of the Station 

(STA) 348.2 frame to detect cracking 

under the stop fittings and intercostal 

flanges at stringers S–14L, S–15L, and 

S–16L, and corrective action if 

necessary. The second existing AD 

currently requires repetitive inspections 

to detect cracking of the intercostal 

webs, attachment clips, and stringer 

splice channels, and corrective action if 

necessary. Since we issued those ADs, 

we have received reports of cracking of 

the STA 348.2 frame above the two 

outboard fasteners attaching the frame 

inner chord and door stop fittings, and 

in the outboard chord at stringer S–16L. 

We have also received reports of 

missing fasteners in the STA 348.2 

frame inner chord. This proposed AD 

would require additional airplanes to do 

the inspection for cracking under the 

stop fittings; extend the repetitive 

interval for certain airplanes; add a onetime inspection to detect missing 

fasteners; and update or add certain 

inspection and repair instructions. This 

proposed AD would also require, for 

certain airplanes, repetitive inspections 

of the cargo barrier net fitting for 

cracking and repair if necessary. This 

proposed AD would also add, for certain 

airplanes, repetitive inspections for 

cracking of the S–15L aft intercostal, 

and repair if necessary. We are 

proposing this AD to detect and correct 

fatigue cracking of the intercostals on 

the forward and aft sides of the forward 

entry door cutout, which could result in 

loss of the forward entry door and rapid 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 12, 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. 

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; 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: 

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: 


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