58982 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 

Messier-Dowty Service Bulletin A33/34–32– 

283 or A33/34–32–284, both including 

Appendix A, both dated May 11, 2010, as 

applicable. 

(l) New Optional Methods of Compliance 

(1) Inspections for corrosion and damage to 

the protective treatment of the bogie beam, 

and repairs, done in accordance with 

Messier-Dowty Service Bulletin A33/34–32– 

278, including appendices A and B, dated 

February 17, 2010, are acceptable methods of 

compliance with the requirements of 

paragraph (i)(1) of this AD. 

(2) Modification of a MLG bogie beam, 

done in accordance with Messier-Dowty 

Service Bulletins A33/34–32–283 and A33/

34–32–284, both including Appendix A, both 

dated May 11, 2010, as applicable, is an 

acceptable method of compliance with the 

requirements of paragraph (i)(2) of this AD. 

(m) New Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a MLG bogie beam on any 

airplane unless it is in compliance with the 

requirements and compliance times of 

paragraphs (g), (h), and (i) of this AD. 

(n) New Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) or (i) of this AD to 

Airbus, Customer Service Directorate, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, using the applicable reporting 

sheet in Airbus Service Bulletin A330–32– 

3237 or A340–32–4279, both dated January 

18, 2011, at the applicable time specified in 

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

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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 

were approved by the State of Design 

Authority (or its delegated agent). For a 

repair method to be approved, the repair 

approval must specifically refer to this AD. 

You are required to ensure the product is 

airworthy before it is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(p) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2012–0015, dated January 23, 2012, for 

related information, which can be found in 

the AD docket on the internet at http://

www.regulations.gov. 

Issued in Renton, Washington, on 

September 17, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23324 Filed 9–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0796; Directorate 

Identifier 2013–NM–111–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 supersede 

airworthiness directive (AD) 2013–07– 

07, which applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series 

airplanes. AD 2013–07–07 requires 

inspecting to determine the part number 

of the attach pins of the horizontal 

stabilizer rear spar, and replacing 

certain attach pins. Since we issued AD 

2013–07–07, we received inquiries from 

affected operators regarding the parts 

installation limitation and prohibition, 

and re-installation of certain attach pins 

that were removed for inspection. This 

proposed AD would clarify the parts 

installation limitation and prohibition, 

and would add a new requirement for 

certain airplanes on which certain 

attach pins were installed. We are 

proposing this AD to prevent premature 

failure of the attach pins, which could 

cause reduced structural integrity of the 

horizontal stabilizer to fuselage 

attachment, resulting in loss of control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; 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, WA. 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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 58983 

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, WA 

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–2013–0796; Directorate Identifier 

2013–NM–111–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 March 28, 2013, we issued AD 

2013–07–07, Amendment 39–17411 (78 

FR 22182, April 15, 2013) (‘‘AD 2013– 

07–07’’), for all Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. AD 2013–07–07 requires 

inspecting to determine the part number 

of the attach pins of the horizontal 

stabilizer rear spar, and replacing 

certain attach pins. For airplanes having 

line numbers 1 through 3534, AD 2013– 

07–07 also prohibited installing attach 

pins having part number (P/N) 

180A1612–3 or 180A1612–4 that have 

56,000 or greater flight cycles, unless 

certain actions had been done. AD 

2013–07–07 resulted from reports of an 

incorrect procedure used to apply the 

wear and corrosion protection surface 

coating to attach pins of the horizontal 

stabilizer rear spar. We issued AD 2013– 

07–07 to prevent premature failure of 

the attach pins, which could cause 

reduced structural integrity of the 

horizontal stabilizer to fuselage 

attachment, resulting in loss of control 

of the airplane. 

Actions Since AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013) Was Issued 

Since we issued AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013), we have received 

inquiries from affected operators 

regarding the parts installation 

limitation and prohibition (i.e., 

paragraph (i)(1)) of AD 2013–07–07, and 

re-installation of certain attach pins of 

the horizontal stabilizer rear spar 

removed for inspection during 

maintenance. 

We have re-reviewed our response to 

commenter Japan Airlines (JAL) in AD 

2013–07–07, Amendment 39–17411 (78 

FR 22182, April 15, 2013), and have 

determined it is necessary to provide 

further clarification. JAL requested 

approval of re-installation of any nondiscrepant attach pins having P/N 

180A1612–3 or 180A1612–4 removed 

for inspection during maintenance. 

We clarify that the term ‘‘install,’’ as 

used in AD 2013–07–07, Amendment 

39–17411 (78 FR 22182, April 15, 2013), 

can be interpreted as meaning ‘‘replace’’ 

while remaining within the intent of AD 

2013–07–07. That is, by simply reinstalling non-discrepant attach pins 

having P/N 180A1612–3 or 180A1612– 

4 on the same airplane from which they 

were removed, the operator is not 

‘‘installing’’ a new or different attach 

pin. Therefore, no alternative method of 

compliance is necessary to re-install 

non-discrepant attach pins having P/N 

180A1612–3 or 180A1612–4 on the 

same airplane from which they were 

removed during maintenance not 

associated with AD 2013–07–07. 

To clarify paragraph (i)(1) of AD AD 

2013–07–07, Amendment 39–17411 (78 

FR 22182, April 15, 2013), for airplanes 

having line numbers 1 through 3534, we 

have removed that paragraph and have 

added new paragraph (k) to this 

proposed AD. New paragraph (k) of this 

proposed AD would provide for 

installation of a attach pin of the 

horizontal stabilizer rear spar having 

P/N 180A1612–3 or 180A1612–4, 

provided it is replaced with an attach 

pin having P/N 180A1612–7 or 

180A1612–8 prior to the accumulation 

of 56,000 total flight cycles on the pin. 

In addition, for those same airplanes, 

paragraph (i)(1) of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013), inadvertently allowed 

installation of an attach pin having P/N 

180A1612–3 or 180A1612–4, even 

though the attach pin had been replaced 

with an attach pin having P/N 

180A1612–7 or 180A1612–8, as 

required by paragraph (h) of AD 2013– 

07–07. In light of this, we have added 

new paragraph (l) to this proposed AD 

for those airplanes on which attach pins 

having P/N 180A1612–3 or 180A1612– 

4 were installed. New paragraph (l) of 

this proposed AD would require 

replacement of those attach pins with 

attach pins having P/N 180A1612–7 or 

180A1612–8 prior to the accumulation 

of 56,000 total flight cycles on the attach 

pin, or within 1,000 flight cycles on the 

airplane after the effective date of this 

AD, whichever occurs later. 

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 

certain requirements of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013). This proposed AD 

would clarify the parts installation 

limitation and prohibition, and would 

add a new requirement for certain 

airplanes on which certain attach pins 

were installed. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,050 airplanes of U.S. registry. 

The new proposed requirements add no 

significant economic burden over that 

specified in AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013). Those costs are 

repeated for the convenience of affected 

operators, as follows: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection and attach pin replacement [retained actions from AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013)].

39 work-hours × $85 

per hour = $3,315.

Up to $6,312 ............. Up to $9,627 ............. Up to $10,108,350. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
58984 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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. 

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) 

2013–07–07, Amendment 39–17411 (78 

FR 22182, April 15, 2013), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2013–0796; Directorate Identifier 2013– 

NM–111–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by November 12, 2013. 

(b) Affected ADs 

(1) This AD supersedes AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). 

(2) This AD affects certain requirements of 

AD 2004–05–19, Amendment 39–13514 (69 

FR 10921, March 9, 2004; corrected April 13, 

2004 (69 FR 19313). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/408E012E008616A786257

8880060456C?Open

Document&Highlight=st00830se) does not 

affect the ability to accomplish the actions 

required by this AD. Therefore, for airplanes 

on which STC ST00830SE is installed, a 

‘‘change in product’’ alternative method of 

compliance (AMOC) approval request is not 

necessary to comply with the requirements of 

14 CFR 39.17. For all other AMOC requests, 

the operator must request approval for an 

AMOC in accordance with the procedures 

specified in paragraph (m) of this AD. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by reports of an 

incorrect procedure used to apply the wear 

and corrosion protection surface coating to 

attach pins of the horizontal stabilizer rear 

spar. We are issuing this AD to prevent 

premature failure of the attach pins, which 

could cause reduced structural integrity of 

the horizontal stabilizer to fuselage 

attachment, resulting in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Part Number Inspection 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). For airplanes having line numbers 

1 through 3534 inclusive: Before the 

accumulation of 56,000 total flight cycles, or 

within 3,000 flight cycles after May 20, 2013 

(the effective date of AD 2013–07–07), 

whichever occurs later, inspect to determine 

the part number of the attach pins of the 

horizontal stabilizer rear spar. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number of 

the attach pin can be conclusively 

determined from that review. 

(h) Retained Replacement 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). If, during the inspection required 

by paragraph (g) of this AD, any horizontal 

stabilizer rear spar attach pin has P/N 

180A1612–3 or 180A1612–4, prior to the 

accumulation of 56,000 total flight cycles on 

the pin, or within 3,000 flight cycles after 

May 20, 2013 (the effective date of AD 2013– 

07–07), whichever occurs later, replace with 

a new attach pin having P/N 180A1612–7 or 

180A1612–8, respectively, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–55–1093, dated April 9, 2012. 

(i) Retained Parts Installation Prohibition 

This paragraph restates the requirements of 

paragraph (i)(2) of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). For airplanes having line numbers 

3535 and subsequent: As of May 20, 2013 

(the effective date of AD 2013–07–07), no 

person may install an attach pin of the 

horizontal stabilizer rear spar having P/N 

180A1612–3 or 180A1612–4 on any airplane. 

(j) Retained Terminating Action for AD 

2004–05–19, Amendment 39 13514 (69 FR 

10921, March 9, 2004; Corrected April 13, 

2004 (69 FR 19313)) 

This paragraph restates the provisions of 

paragraph (j) of AD 2013–07–07, Amendment 

39–17411 (78 FR 22182, April 15, 2013). 

Accomplishment of the actions required by 

paragraphs (g) and (h) of this AD terminates 

the requirements of paragraphs (a), (b), (c), 

(d), and (e) of AD 2004–05–19, Amendment 

39–13514 (69 FR 10921, March 9, 2004; 

corrected April 13, 2004 (69 FR 19313)), for 

the rear spar attach pins only. 

(k) New Parts Installation Limitation 

For airplanes having line numbers 1 

through 3534 inclusive: As of the effective 

date of this AD, an attach pin of the 

horizontal stabilizer rear spar having P/N 

180A1612–3 or 180A1612–4 may be installed 

on an airplane, provided it is replaced with 

an attach pin having P/N 180A1612–7 or 

180A1612–8, as applicable, prior to the 

accumulation of 56,000 total flight cycles on 

the attach pin. The replacement must be 

done in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–55– 

1093, dated April 9, 2012. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 58985 

(l) New Attach Pin Replacement 

For airplanes having line numbers 1 

through 3534 inclusive on which an attach 

pin of the horizontal stabilizer rear spar 

having P/N 180A1612–7 or 180A1612–8 has 

been replaced with an attach pin having P/ 

N 180A1612–3 or 180A1612–4 before the 

effective date of this AD: Prior to the 

accumulation of 56,000 total flight cycles on 

the pin, or within 1,000 flight cycles on the 

airplane after the effective date of this AD, 

whichever occurs later, replace the attach pin 

having P/N 180A1612–3 or 180A1612–4 with 

an attach pin having P/N 180A1612–7 or 

180A1612–8, as applicable, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–55–1093, dated April 9, 2012. 

(m) 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 

paragraph (n)(1) of this AD. Information may 

be emailed to 9-ANM-Seattle-ACO-AMOCRequests-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, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013), are approved as AMOCs for the 

corresponding provisions of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6590; 

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; 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 

September 17, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23274 Filed 9–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DELAWARE RIVER BASIN 

COMMISSION 

18 CFR Part 410 

Proposed Amendments to the Water 

Quality Regulations, Water Code and 

Comprehensive Plan To Update Water 

Quality Criteria for pH 

AGENCY: Delaware River Basin 

Commission. 

ACTION: Proposed rule; notice of public 

hearing. 

SUMMARY: The Commission will hold a 

public hearing to receive comments on 

proposed amendments to the 

Commission’s Water Quality 

Regulations, Water Code and 

Comprehensive Plan to update stream 

quality objectives (also called ‘‘water 

quality criteria’’) for pH in interstate 

tidal and non-tidal reaches of the main 

stem Delaware River. 

DATES: The public hearing will be held 

at 2 p.m. on Thursday, October 24, 

2013. The hearing will continue until all 

those wishing to testify have had an 

opportunity to do so. Written comments 

will be accepted and must be received 

by 5 p.m. on Thursday, November 21, 

2013. For more information regarding 

the procedures for the hearing and 

comments, see Supplementary 

Information. 

ADDRESSES: The public hearing will be 

held in the Goddard Conference Room 

at the Commission’s office building 

located at 25 State Police Drive, West 

Trenton, NJ. As Internet mapping tools 

are inaccurate for this location, please 

use the driving directions posted on the 

Commission’s Web site. 

Oral Testimony and Written 

Comments: Persons wishing to testify at 

the hearing are asked to register in 

advance by phoning Paula Schmitt at 

609–883–9500, ext. 224. Written 

comments may be submitted as follows: 

If by email, to paula.schmitt@

drbc.state.nj.us; if by fax, to 

Commission Secretary at 609–883–9522; 

if by U.S. Mail, to Commission 

Secretary, DRBC, P.O. Box 7360, West 

Trenton, NJ 08628–0360; and if by 

overnight mail, to Commission 

Secretary, DRBC, 25 State Police Drive, 

West Trenton, NJ 08628–0360. 

Comments also may be delivered by 

hand at any time during the 

Commission’s regular office hours 

(Monday through Friday, 8:30 a.m. 

through 5 p.m. except on national 

holidays) until the close of the comment 

period at 5 p.m. on Thursday, November 

21, 2013. In all cases, please include the 

commenter’s name, address and 

affiliation, if any, in the comment 

document and ‘‘pH Rulemaking’’ in the 

subject line. 

FOR FURTHER INFORMATION CONTACT: The 

rule text and a report entitled ‘‘pH 

Criteria Revision Recommendations for 

Interstate Waters of the Delaware River 

Basin: Basis & Background Document’’ 

(DRBC, March 2013) are available on the 

Commission’s Web site, www.drbc.net. 

Hard copies of the latter document may 

be obtained for the price of postage by 

contacting Ms. Paula Schmitt at 609– 

883–9500, ext. 224. For questions about 

the technical basis for the rule, please 

contact Dr. Erik Silldorff at 609–883– 

9500 ext. 234. For queries about the 

rulemaking process, please contact 

Pamela Bush at 609–477–7203. 

SUPPLEMENTARY INFORMATION:

Background. The Commission in 1967 

assigned stream quality objectives (also 

called ‘‘criteria’’) for pH to all tidal and 

non-tidal interstate streams in the 

Delaware River Basin (‘‘basin’’). Since 

that time, scientists’ understanding of 

natural fluctuations in freshwater and 

saltwater pH levels has grown. 

Likewise, the development and 

application of pH criteria have evolved, 

while the Commission’s pH stream 

quality objectives have remained 

unchanged. Commission scientists in 

consultation with experts from DRBC 

member states and federal agencies have 

evaluated the pH criteria adopted by 

signatory states and recommended by 

federal agencies over the past four-anda-half decades. They have concluded 

that in order to minimize regulatory 

inconsistencies and better address 

natural pH cycles in the main stem 

Delaware River, two classes of revisions 

to the Commission’s criteria for this 

shared interstate waterway should be 

considered. The first concerns the range 

of pH levels deemed to comprise the 

numeric standard within the tidal and 

non-tidal zones of the main stem and 

tidal portions of tributaries. The second 

concerns excursions outside the 

standard range that are attributable to 

natural conditions. The proposed 

revisions were unanimously endorsed 

by the Commission’s Water Quality 

Advisory Committee (‘‘WQAC’’) in 

March 2009. The WQAC is a standing 

committee of stakeholders, including 

regulators, municipal and industrial 

dischargers, academicians and 


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