38066 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–46, dated December 14, 

2009; Bombardier Service Bulletin 8–32–166, 

Revision A, dated January 29, 2009; and 

Bombardier Service Bulletin 84–32–57, 

Revision A, dated June 15, 2009; for related 

information. 

Issued in Renton, Washington, on June 23, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–15983 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0646; Directorate 

Identifier 2009–NM–223–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 727, 727C, 727–100, 

727–100C, 727–200, and 727–200F 

Series 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 

Model 727, 727C, 727–100, 727–100C, 

727–200, and 727–200F series airplanes. 

This proposed AD would require 

repetitive detailed inspections of the aft 

pressure bulkhead web for cracking, and 

repair if necessary. For certain 

airplanes, this proposed AD also would 

provide for an optional preventative 

modification of the aft pressure 

bulkhead web, which would terminate 

certain repetitive detailed inspections. 

This proposed AD results from reports 

of cracks in the aft pressure bulkhead 

web. We are proposing this AD to detect 

and correct cracking in the aft pressure 

bulkhead web, which could adversely 

affect the structural integrity of the 

airplane, resulting in difficulty 

maintaining cabin pressurization or 

rapid decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 16, 2010. 

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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

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–2010–0646; Directorate Identifier 

2009–NM–223–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 13 reports of cracks 

in the aft pressure bulkhead web 

ranging from 0.75 inch to 11.8 inches in 

length at the buttock line 61, between 

water line (WL) 220 and WL 228. The 

cracks originated at the hydraulic line 

support brackets, which were installed 

in production after airplane line number 

1136, or in accordance with Boeing 

Service Bulletin 727–29–0057. The 

cracks were found in airplanes that had 

accumulated between 14,939 total flight 

hours and 39,369 total flight hours, and 

between 10,685 total flight cycles and 

29,357 total flight cycles. The cracking 

is attributed to fatigue of the aft pressure 

bulkhead web due to vibrations from the 

number 1 engine hydraulic pump line, 

in addition to normal pressurization 

cycles. Material analysis revealed 

multiple crack initiation sites and no 

evidence of corrosion. This condition, if 

not corrected, could result in difficulty 

maintaining cabin pressurization or 

rapid decompression of the airplane. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 727–53– 

0232, dated September 23, 2009. This 

service bulletin describes procedures for 

initial and repetitive detailed 

inspections of the aft pressure bulkhead 

web for any cracking around the 

hydraulic line support bracket, and 

repair of any crack found. For certain 

airplanes, this service bulletin describes 

procedures for installing an optional 

preventative modification if no cracking 

is found during the detailed inspections. 

The preventative modification includes 

doing high frequency eddy current 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 38067 

(HFEC) inspections of the open fastener 

holes and installing a modification 

doubler on the aft side of the bulkhead 

web, which would eliminate the need 

for certain repetitive inspections. If any 

cracking is found during the detailed or 

HFEC inspection, this service bulletin 

specifies contacting Boeing for repair 

instructions and installing the repair. 

The compliance times for the initial 

inspection range between 3,500 flight 

cycles from the date on the service 

bulletin and 7,000 flight cycles since the 

previous inspection. The compliance 

time for repairing any cracking is before 

further flight. The interval for repeating 

the detailed inspection ranges between 

1,000 flight cycles and 12,000 flight 

cycles, depending on airplane 

configuration, the time since the last 

inspection, and the type of the last 

inspection. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and the Service 

Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Boeing Special Attention Service 

Bulletin 727–53–0232, dated September 

23, 2009, 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. 

Boeing Special Attention Service 

Bulletin 727–53–0232, dated September 

23, 2009, provides damage tolerance 

inspections in Table 3 of paragraph 1.E. 

of that service bulletin. Note 1 of this 

proposed AD relates to these damage 

tolerance inspections, which are not 

required for compliance with this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 243 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per product Number of U.S.-registered airplanes Fleet cost 

Detailed inspection, 

per inspection cycle.

1 $85 None ........................ $85, per inspection 

cycle.

243 .......................... $20,655, per inspection cycle. 

Preventative modification.4 $85 Negligible1 ............... $340 ........................ Up to 243 ................ Up to $82,620. 

1 The cost of material for the modification would depend on the size and location of the repair; the materials necessary for the modification are 

standard shop materials that would be provided out of the operator’s stock. 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance 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: 

The Boeing Company: Docket No. FAA– 

2010–0646; Directorate Identifier 2009– 

NM–223–AD. 

Comments Due Date 

(a) We must receive comments by August 

16, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 727, 727C, 727–100, 727– 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

38068 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 

100C, 727–200, and 727–200F series 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of cracks 

in the aft pressure bulkhead web. The 

Federal Aviation Administration is issuing 

this AD to prevent cracking in the aft 

pressure bulkhead web, which could 

adversely affect the structural integrity of the 

airplane, resulting in difficulty maintaining 

cabin pressurization or rapid decompression 

of the airplane. 

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. 

Repetitive Inspections and Corrective 

Actions 

(g) At the applicable initial compliance 

time specified in Tables 1 and 2 of paragraph 

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

Attention Service Bulletin 727–53–0232, 

dated September 23, 2009 (‘‘the service 

bulletin’’); except as provided by paragraph 

(j) of this AD: Perform a detailed inspection 

for cracking in the area around the hydraulic 

line support bracket on the aft side of the aft 

pressure bulkhead web between water line 

(WL) 217 to WL 230, and buttock line (BL) 

48 left to BL 66 left. Do the inspection in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(1) For Group 1, Configuration 1 airplanes, 

and Group 2 airplanes, as identified in the 

service bulletin: If no cracking is found 

during the inspection required by paragraph 

(g) of this AD, do the actions specified in 

paragraph (g)(1)(i) or (g)(1)(ii) of this AD in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(i) Accomplish the preventative 

modification specified in PART 3 of the 

service bulletin before further flight. 

(ii) Repeat the detailed inspection at the 

applicable interval specified in Tables 1 and 

2 of paragraph 1.E., ‘‘Compliance,’’ of the 

service bulletin. Accomplishing the 

preventative modification specified in 

paragraph (g)(1)(i) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(2) For Group 1, Configuration 2 airplanes, 

as identified in the service bulletin: If no 

cracking is found during the inspection 

required by paragraph (g) of this AD, repeat 

the detailed inspection at the applicable 

interval specified in Tables 1 and 2 of 

paragraph 1.E., ‘‘Compliance,’’ of the service 

bulletin. 

Note 1: The damage tolerance inspections 

specified in Table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 727–53–0232, dated 

September 23, 2009, 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)). 

(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 Special Attention Service Bulletin 

727–53–0232, dated September 23, 2009; 

except as provided by paragraph (i) of this 

AD. 

(i) If any cracking is found during any 

inspection required by this AD, and Boeing 

Special Attention Service Bulletin 727–53– 

0232, dated September 23, 2009, specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the cracking using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(j) Where Boeing Special Attention Service 

Bulletin 727–53–0232, dated September 23, 

2009, specifies a compliance time after the 

date on that service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

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

917–6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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. 

Issued in Renton, Washington, on June 25, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–15989 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Parts 122, 123, 403, 501 and 

503 

[FRL–9169–8] 

Public Meeting With Interested 

Stakeholders for National Pollutant 

Discharge Elimination System 

(NPDES) Electronic Reporting Rule 

AGENCY: Environmental Protection 

Agency. 

ACTION: Notice of public meeting. 

SUMMARY: The United States 

Environmental Protection Agency (EPA) 

gives notice of a meeting to discuss the 

NPDES Electronic Reporting Rule. With 

this rulemaking, EPA is utilizing 21st 

Century modern technologies to 

improve management and performance 

of the NPDES program by requiring 

electronic reporting of NPDES 

information from regulated facilities. 

This will reduce the burden for facilities 

to report to regulatory agencies and for 

states to report to EPA. Expected 

benefits include lower processing costs 

for facilities and states, improved data 

quality and accuracy, greater data 

accessibility and transparency for the 

public, and an increased ability to target 

and address noncompliance that will 

improve and protect water quality. This 

meeting will be a session in which EPA 

will discuss electronic reporting 

alternatives for submission of NPDES 

information directly to states and/or 

EPA from permittees. Topics include 

the feasibility of requiring electronic 

reporting in areas such as electronic 

discharge monitoring reports (eDMRs), 

electronic notice of intent (eNOI), and 

electronic program reports. The purpose 

of this meeting is to give interested 

parties the opportunity to discuss the 

proposed rule and to provide EPA 

feedback on the presented options. 

DATES: The meeting will be held on 

Tuesday, July 13, 2010 from 1 p.m. till 

3 p.m. 

ADDRESSES: The meeting location is 

Room 1117A EPA East, 1201 

Constitution Ave., NW., Washington, 

DC 20460. 

FOR FURTHER INFORMATION CONTACT: 

Anuj Vaidya 202–564–3459, 

vaidya.anuj@epa.gov or Sharon Gonder 

202–564–5256, gonder.sharon@epa.gov. 

If you are interested in attending this 

meeting, please contact Mr. Anuj Vaidya 

or Ms. Sharon Gonder to register for this 

meeting no later than Wednesday, July 

7, 2010. 

SUPPLEMENTARY INFORMATION: This 

meeting will be open to all stakeholders 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS