81890 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$88,120, or $11,015 per product. 

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: 

Saab AB, Saab Aerosystems: Docket No. 

FAA–2011–1410; Directorate Identifier 2011– 

NM–033–AD. 

Comments Due Date 

(a) We must receive comments by February 

13, 2012. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Saab AB, Saab 

Aerosystems Model SAAB 2000 airplanes, all 

serial numbers; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic Power. 

Reason 

(e) This AD was prompted by reports of 

hydraulic accumulator failure. We are issuing 

this AD to prevent failure of hydraulic 

accumulators, which may result in damage to 

the airplane and injury to occupants. 

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 12 months after the effective 

date of this AD, replace all hydraulic 

accumulators having part number (P/N) 08 

8423 030 1, with stainless steel hydraulic 

accumulators having P/N 40800–2050, and 

do the structural modifications in the nose 

landing gear bay, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 2000–29–024, Revision 01, dated 

November 5, 2010. 

Parts Installation 

(h) After replacement of hydraulic 

accumulators having P/N 08 8423 030 1 with 

hydraulic accumulators having P/N 40800– 

2050, and doing the structural modifications 

in the nose landing gear bay, as required by 

paragraph (g) of this AD, no person may 

install any hydraulic accumulator having P/ 

N 08 8423 030 1 on any airplane. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Replacing the hydraulic accumulators 

and doing the structural modifications in the 

nose landing gear bay, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 2000–29–024, dated November 18, 

2009, before the effective date of this AD, is 

acceptable for compliance with the 

corresponding replacement and structural 

modifications required by paragraph (g) of 

this AD. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; 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 

(k) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0004, dated January 17, 2011; and Saab 

Service Bulletin 2000–29–024, Revision 01, 

dated November 5, 2010; for related 

information. 

Issued in Renton, Washington, on 

December 19, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–33275 Filed 12–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1326; Directorate 

Identifier 2010–NM–177–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


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SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to The Boeing Company 

Model 757–200, –200CB, and –300 

series airplanes. The existing AD 

currently requires initial and repetitive 

inspections of the fuselage skin and bear 

strap at the forward, upper corner of the 

L1 entry door cutout for cracking, and 

repair if necessary. That action also 

provides an optional terminating action 

for the repetitive inspections. Since we 

issued that AD, we have received 

reports of additional cracking in the 

fuselage skin. This proposed AD would 

add inspections for airplanes having 

repairs or preventative modifications 

installed and supplemental inspections 

for certain airplanes. This proposed AD 

also would add airplanes to the 

applicability. We are proposing this AD 

to detect and correct cracking of the 

fuselage skin and bear strap at the 

forward, upper corner of the L1 entry 

door cutout, which could result in 

reduced structural integrity of the L1 

entry door and consequent rapid 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by February 13, 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: 

Nancy Marsh, 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: 

nancy.marsh@faa.gov. 

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–2011–1326; Directorate Identifier 

2010–NM–177–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 

On April 28, 2004, we issued AD 

2004–09–32, Amendment 39–13622 (69 

FR 25481, May 7, 2004), for certain 

Model 757–200 series airplanes. That 

AD requires initial and repetitive 

inspections of the fuselage skin and bear 

strap at the forward, upper corner of the 

L1 entry door cutout for cracking, and 

repair if necessary. That AD also 

provides an optional terminating action 

for the repetitive inspections. That AD 

resulted from reports of cracking in the 

fuselage skin and bear strap at the 

forward, upper corner of the L1 entry 

door cutout. We issued that AD to detect 

and correct cracking of the fuselage skin 

and bear strap at the forward, upper 

corner of the L1 entry door cutout, 

which could result in reduced structural 

integrity of the L1 entry door and 

consequent rapid decompression of the 

airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, 

May 7, 2004), we have received reports 

of additional cracking in the fuselage 

skin. We also have determined that all 

Model 757–200, –200CB, and –300 

series airplanes may be subject to the 

unsafe condition, and that the existing 

actions may not adequately address the 

unsafe condition. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 757–53– 

0094, Revision 1, dated August 12, 

2009. The service information describes 

procedures for the following repetitive 

inspections, depending on 

configuration: 

• High frequency eddy current 

(HFEC) and low frequency eddy current 

(LFEC) inspections for cracking of the 

skin and bear strap at the forward upper 

corner of the L1 entry door cutout. 

• Supplemental HFEC and LFEC 

inspections for cracking of the bear strap 

and inner chord strap on airplanes 

having a repair doubler, tripler, and 

quadrupler installed. 

• Supplemental HFEC, LFEC, and 

detailed inspections for cracking of the 

skin, bear strap, doubler, tripler, and 

quadrupler on airplanes having a repair 

doubler, tripler, and quadrupler 

installed. 

• Supplemental HFEC, LFEC, and 

detailed inspections for cracking of the 

skin, bear strap, inner chord strap, 

doubler, and tripler on airplanes having 

a repair doubler and tripler installed. 

• Supplemental HFEC, LFEC, and 

detailed inspections for cracking of the 

skin, bear strap, and doubler on 

airplanes having a preventive 

modification doubler installed. 

• Supplemental HFEC and LFEC 

inspections for cracking of the bear strap 

and inner chord strap on airplanes 

having a doubler installed. 

That service bulletin also provides 

procedures for corrective actions, which 

include repairing certain cracks, and 

contacting Boeing for certain other 

repair instructions. 

The compliance times for the initial 

inspections are either before 22,000 total 

flight cycles or within 500 flight cycles 

after the issue date on Boeing Special 

Attention Service Bulletin 757–53– 

0094, dated January 16, 2008, whichever 

occurs later; or within 12,000 flight 

cycles after the modification, or within 

500 flight cycles after the issue date on 

Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, whichever occurs 

later; depending on configuration. The 


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repetitive inspection interval for these 

inspections is 1,400 flight cycles. 

The compliance times for the initial 

supplemental inspections are 37,500 

total flight cycles (for inspection of the 

skin, bear strap, doubler, and tripler), or 

50,000 total flight cycles (for inspection 

of the bear strap and inner chord strap). 

The repetitive inspection interval for 

these inspections is either 4,000 flight 

cycles or 12,000 flight cycles, depending 

on configuration. 

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 retain all 

requirements of AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, 

May 7, 2004). This proposed AD would 

add inspections for airplanes having 

repairs or preventative modifications 

installed, and supplemental inspections 

for certain airplanes; and repair, if 

necessary. This proposed AD also 

would add airplanes to the applicability 

of the existing AD. 

Exceptions to Certain Compliance 

Times 

The service bulletin specifies to do 

certain HFEC, LFEC, and detailed 

inspections before the accumulation of 

37,500 total flight cycles. However, in 

order to address airplanes that might 

have already exceeded that threshold, 

this proposed AD would require the 

inspections to be accomplished at the 

latest of the times below: 

• Before the accumulation of 37,500 

total flight cycles. 

• Within 4,000 flight cycles since 

installation of the modification. 

• Within 24 months after the effective 

date of this AD. 

Changes to Existing AD 

This proposed AD would retain all 

requirements of AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, 

May 7, 2004). Since AD 2004–09–32 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2004–09–32 

Corresponding 

requirement in this 

proposed AD 

paragraph (a) paragraph (g) 

paragraph (b) paragraph (h) 

paragraph (c) paragraph (i) 

paragraph (d) paragraph (j) 

Boeing Commercial Airplanes has 

received an Organization Designation 

Authorization (ODA). We have revised 

paragraph (i) of this proposed AD to 

delegate the authority to approve an 

alternative method of compliance for 

any repair required by this proposed AD 

to the Boeing Commercial Airplanes 

ODA rather than a Designated 

Engineering Representative (DER). 

Costs of Compliance 

We estimate that this proposed AD 

affects 591 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Work-hours Average labor 

rate per hour Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections (retained actions 

from existing AD).

2 $85 $170 per inspection cycle ..... 57 $9,690 per inspection cycle. 

Inspection (new proposed action).3 85 $255 per inspection cycle ..... 591 $150,705 per inspection 

cycle. 

Supplemental inspection ....... 15 85 $1,275 per inspection cycle .. 591 $753,525 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

proposed inspections. 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 ............................................ Up to 26 work-hours × $85 = Up 

to $2,210 

Up to $2,661 ................................. Up to $4,871 depending on configuration. 

Preventive modification .................. 18 work-hours × $85 = $1,530 $1,338 ........................................... $2,868. 

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 

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. 


wreier-aviles on DSK3TPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules 81893 

For the reasons discussed above, I 

certify that the 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 

removing airworthiness directive (AD) 

2004–09–32, Amendment 39–13622 (69 

FR 25481, May 7, 2004), and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2011–1326; Directorate Identifier 2010– 

NM–177–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by February 13, 2012. 

(b) Affected ADs 

This AD supersedes AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, May 7, 

2004). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 757–200, –200CB, and –300 

series airplanes; certificated in any category. 

(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 cracks 

in the fuselage skin and bear strap at the 

forward upper corner of the L1 entry door 

cutout. We are issuing this AD to detect and 

correct cracking of the fuselage skin and bear 

strap at the forward, upper corner of the L1 

entry door cutout, which could result in 

reduced structural integrity of the L1 entry 

door and consequent rapid decompression of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2004–09–32, AMENDMENT 39–13622 (69 

FR 25481, MAY 7, 2004), WITH NEW 

TERMINATING ACTION 

(g) Initial Inspections 

For airplanes having line numbers 1 

through 90 inclusive: Within 500 flight 

cycles after May 24, 2004 (the effective date 

of AD 2004–09–32 Amendment 39–13622 (69 

FR 25481, May 7, 2004)), or within 90 days 

after May 24, 2004, whichever occurs later, 

do the inspections of the forward, upper 

corner of the L1 entry door cutout specified 

in paragraphs (g)(1), (g)(2), and (g)(3) of this 

AD, per Part 1 of the Work Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0089, dated March 18, 2004, until 

the initial inspection required by paragraph 

(k) of this AD has been done. Doing the repair 

specified in paragraph (i) or (l) of this AD, 

or doing the preventive modification 

specified in paragraph (j) of this AD, 

terminates the inspection required by this 

paragraph. 

(1) Do a high frequency eddy current 

(HFEC) inspection for cracking of the 

fuselage skin around the adjacent fasteners. 

(2) Do an HFEC inspection for cracking 

along the edge of the skin and bear strap. 

(3) Do a low frequency eddy current (LFEC) 

inspection of the bear strap. 

(h) No Crack Detected: Repetitive 

Inspections and New Terminating 

Modification 

If no crack is detected during any 

inspection required by paragraph (g) of this 

AD: Repeat the inspections required by 

paragraph (g) of this AD at intervals not to 

exceed 1,400 flight cycles, until the 

requirements of paragraph (k) are done. 

Doing the repair specified in paragraph (l) of 

this AD, or doing the preventive modification 

specified in paragraph (j) of this AD, as 

applicable, terminates the repetitive 

inspections required by this paragraph. 

(i) Any Crack Detected: Repair, With New 

Repair Option 

If any crack is detected during any 

inspection required by paragraph (g) or (h) of 

this AD, and Boeing Special Attention 

Service Bulletin 757–53–0089, dated March 

18, 2004, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair, in accordance with a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA; or in 

accordance with data meeting the type 

certification basis of the airplane approved 

by a Boeing Company Organization 

Designation Authorization who has been 

authorized by the Manager, Seattle ACO, to 

make such findings, or using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. For a 

repair method to be approved, the approval 

must specifically reference this AD. Doing 

the repair terminates the inspections required 

by paragraphs (g) and (h) of this AD. 

(j) Optional Preventive Modification 

As an alternative to accomplishing the 

inspections required by paragraphs (g) and 

(h) of this AD, do the optional preventative 

modification of the forward, upper corner of 

the L1 entry door cutout, and do all 

applicable related investigative/corrective 

actions, by accomplishing all the actions 

specified in Part 2 of the Work Instructions 

of Boeing Special Attention Service Bulletin 

757–53–0089, dated March 18, 2004. 

Accomplishment of the modification 

constitutes terminating action for the 

inspections required by paragraphs (g) and 

(h) of this AD. 

New Requirements of This AD 

(k) Inspections 

For airplanes in Group 1, Configurations 1– 

2, and Group 2, Configuration 1, as identified 

in Boeing Special Attention Service Bulletin 

757–53–0094, Revision 1, dated August 12, 

2009: At the applicable times specified in 

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

Special Attention Service Bulletin 757–53– 

0094, Revision 1, dated August 12, 2009, do 

HFEC and LFEC inspections for cracking of 

the skin and bear strap at the forward upper 

corner of the L1 entry door cutout, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0094, Revision 1, 

dated August 12, 2009. Repeat the 

inspections thereafter at intervals not to 

exceed 1,400 flight cycles. Doing the initial 

inspection required by this paragraph 

terminates the inspections required by 

paragraphs (g) and (h) of this AD. Doing the 

repair specified in paragraph (l) of this AD, 

or doing the optional preventive modification 

specified in paragraph (m) of this AD, 

terminates the inspections required by this 

paragraph. 

(l) Repair 

If any cracking is found during any 

inspection required by paragraph (k) of this 

AD, before further flight, repair, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0094, Revision 1, 

dated August 12, 2009; except as required by 

paragraph (p)(3) of this AD. Doing the repair 

terminates the repetitive inspections required 

by paragraph (k) of this AD. 

(m) Optional Preventive Modification 

Accomplishment of the optional 

preventive modification, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0094, Revision 1, dated August 12, 2009, 

terminates the repetitive inspections required 

by paragraph (k) of this AD. 

(n) Supplemental Inspections and Repair 

For airplanes in Group 1, Configurations 

3–5, and Group 2, Configurations 2–4 as 

identified in Boeing Special Attention 

Service Bulletin 757–53–0094, Revision 1, 

dated August 12, 2009; on which a repair 

doubler, tripler, or quadrupler is installed, or 

on which a preventive modification doubler 


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is installed: At the applicable times in 

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

Special Attention Service Bulletin 757–53– 

0094, Revision 1, dated August 12, 2009, 

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

AD, do LFEC, HFEC, and detailed 

inspections, as applicable, for cracking of the 

doubler, tripler, quadrupler, skin, bear strap, 

and inner chord strap, as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0094, Revision 1, 

dated August 12, 2009. Repeat the 

inspections thereafter at the applicable times 

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

Boeing Special Attention Service Bulletin 

757–53–0094, Revision 1, dated August 12, 

2009. 

(o) Supplemental Repair 

If any cracking is found during any 

inspection required by paragraph (n) of this 

AD, before further flight, repair the crack in 

accordance with the procedures specified in 

paragraph (q) of this AD. 

(p) Exceptions to Service Bulletin 

Specifications 

The following exceptions apply to this AD. 

(1) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies a compliance time 

after the ‘‘original issue date’’ or ‘‘Revision 1 

date of the service bulletin,’’ this AD requires 

compliance after the effective date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies doing the HFEC, 

LFEC, and detailed inspections required by 

paragraph (n) of this AD before the 

accumulation of 37,500 total flight cycles, 

this AD requires the inspections to be 

accomplished at the latest of the times 

specified in paragraphs (p)(2)(i) and (p)(2)(ii) 

of this AD. 

(i) Before the accumulation of 37,500 total 

flight cycles. 

(ii) Within 24 months after the effective 

date of this AD. 

(3) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies contacting Boeing 

for repair instructions, this AD requires 

repairing in accordance with the procedures 

specified in paragraph (q) of this AD. 

(q) 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 ACO, send it to ATTN: Nancy Marsh, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 917– 

6440; fax: (425) 917–6432; email: 

nancy.marsh@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. 

(4) AMOCs approved for AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, May 7, 

2004), are approved as AMOCs for the 

corresponding actions in paragraphs (g), (h), 

and (i) of this AD. 

(r) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6440; fax: 

(425) 917–6432; email: nancy.marsh@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; 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 

December 16, 2011. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–33355 Filed 12–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1325; Directorate 

Identifier 2010–NM–250–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all EMBRAER Model ERJ 

170 airplanes. The existing AD currently 

requires revising the Airworthiness 

Limitations Section (ALS) of the 

Instructions for Continued 

Airworthiness (ICA) to incorporate new 

structural inspection requirements. 

Since we issued that AD, during full 

scale fatigue testing, cracks were found 

in certain structural components of the 

airplane. Analysis of these cracks 

resulted in manufacturer modifications 

of the ALS of Embraer ERJ 170 

Maintenance Review Board Report 

(MRBR), which include new inspections 

tasks, or modification of the current 

tasks and their respective thresholds 

and intervals. This proposed AD would 

revise the maintenance program to 

incorporate new or revised structural 

inspection requirements. We are 

proposing this AD to detect and correct 

fatigue cracking which could result in 

the loss of structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 13, 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 W12–140, 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 


wreier-aviles on DSK3TPTVN1PROD with PROPOSALS