Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations 13271 

141, 145(g), 148, 218(a) (42 U.S.C. 10137(a), 

10152, 10153, 10154, 10155, 10157, 10161, 

10165(g), 10168, 10198(a)) 44 U.S.C. 3504 

note. 

■ 2. In § 72.214, Certificate of 

Compliance 1014 is revised to read as 

follows: 

§ 72.214 List of approved spent fuel 

storage casks. 

* * * * * 

Certificate Number: 1014. 

Initial Certificate Effective Date: May 

31, 2000. 

Amendment Number 1 Effective Date: 

July 15, 2002. 

Amendment Number 2 Effective Date: 

June 7, 2005. 

Amendment Number 3 Effective Date: 

May 29, 2007. 

Amendment Number 4 Effective Date: 

January 8, 2008. 

Amendment Number 5 Effective Date: 

July 14, 2008. 

Amendment Number 6 Effective Date: 

August 17, 2009. 

Amendment Number 7 Effective Date: 

December 28, 2009. 

Amendment Number 8 Effective Date: 

May 2, 2012, as corrected on November 

16, 2012 (ADAMS Accession No. 

ML12213A170). 

Amendment Number 9 Effective Date: 

March 11, 2014. 

Amendment Number 10 Effective 

Date: May 31, 2016. 

SAR Submitted by: Holtec 

International. 

SAR Title: Final Safety Analysis 

Report for the HI–STORM 100 Cask 

System. 

Docket Number: 72–1014. 

Certificate Expiration Date: May 31, 

2020. 

Model Number: HI–STORM 100. 

* * * * * 

Dated at Rockville, Maryland, this 2nd day 

of March, 2016. 

For the Nuclear Regulatory Commission. 

Victor M. McCree, 

Executive Director of Operations. 

[FR Doc. 2016–05711 Filed 3–11–16; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4222; Directorate 

Identifier 2016–NM–017–AD; Amendment 

39–18433; AD 2016–06–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–300, –400, 

and –500 series airplanes. This AD 

requires repetitive inspections for 

cracking in the horizontal and vertical 

flanges of the rear spar upper chord of 

the horizontal stabilizer, and related 

investigative and corrective actions if 

necessary. This AD was prompted by a 

report of cracking in the center section 

of the horizontal stabilizer. We are 

issuing this AD to detect and correct 

cracking of the rear spar center section 

of the horizontal stabilizer that could 

lead to departure of the horizontal 

stabilizer from the airplane. 

DATES: This AD is effective March 29, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 29, 2016. 

We must receive comments on this 

AD by April 28, 2016. 

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: 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 final rule, 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 view 

this 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

4222. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

4222; 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 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: 

Payman Soltani, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5313; fax: 562–627–5210; 

email: Payman.Soltani@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received a report of cracking 

in the center section of the horizontal 

stabilizer. A review of empennage 

loading of the Model 737–300, –400, 

and –500 series airplanes identified 

several loading discrepancies that 

included landing rollout (LRO) buffet 

condition within the ground-air-ground 

(GAG) operational loads. These loading 

discrepancies impact the operating 

stress level on the rear spar upper chord 

of the horizontal stabilizer center 

section, which can lead to cracking. We 

have determined that the inspection 

threshold for detecting the cracking 

needs to be lower than the existing 

required compliance threshold of 66,000 

total flight cycles. This horizontal 

stabilizer center section cracking, if not 

corrected, could result in departure of 

the horizontal stabilizer from the 

airplane. 

Related Rulemaking 

On April 8, 2008, we issued AD 2008– 

09–13, Amendment 39–15494 (73 FR 

24164, May 2, 2008), for all Boeing 

Model 737–300, –400, and –500 series 


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13272 Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations 

airplanes. AD 2008–09–13 requires 

revising the FAA-approved maintenance 

or inspection program to include 

inspections that will give no less than 

the required damage tolerance rating for 

each structural significant item (SSI), 

doing repetitive inspections to detect 

cracks of all SSIs, and repairing cracked 

structure. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–55A1100, dated January 

26, 2016. This service information 

describes procedures for inspections for 

cracking in the horizontal and vertical 

flanges of the rear spar upper chord of 

the horizontal stabilizer, an inspection 

to identify the fasteners common to the 

rear spar upper chord upper gusset of 

the horizontal stabilizer center section, 

and related investigative and corrective 

actions if necessary. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

FAA’s Determination 

We are issuing 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. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between this AD and the Service 

Information.’’ For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

4222. 

The phrase ‘‘related investigative 

actions’’ is used in this AD. Related 

investigative actions are follow-on 

actions that (1) are related to the 

primary action, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this AD. Corrective actions are 

actions that correct or address any 

condition found. Corrective actions in 

an AD could include, for example, 

repairs. 

Differences Between the AD and the 

Service Information 

Boeing Alert Service Bulletin 737– 

55A1100, dated January 26, 2016, 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this 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 Alert Service Bulletin 737– 

55A1100, dated January 26, 2016, 

specifies compliance using ‘‘horizontal 

stabilizer center section flight cycles’’ or 

‘‘center section flight cycles;’’ this AD 

requires compliance for those 

conditions or compliance times in terms 

of airplane flight cycles. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because cracking of the rear spar 

center section of the horizontal 

stabilizer could lead to departure of the 

horizontal stabilizer from the airplane. 

Therefore, we find that notice and 

opportunity for prior public comment 

are impracticable and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2016–4222 and Directorate 

Identifier 2016–NM–017–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 400 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

Inspections ............. Up to 15 work-hours × $85 per hour = 

$1,275 per inspection cycle.

$0 Up to $1,275 per inspection 

cycle.

Up to $510,000 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair ............................................................... 8 work-hours × $85 per hour = $680 ....................................... (1) $680 

1We have received no definitive data that would enable us to provide parts cost estimates for the actions specified in this AD. 


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Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations 13273 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–06–02 The Boeing Company: 

Amendment 39–18433; Docket No. 

FAA–2016–4222; Directorate Identifier 

2016–NM–017–AD. 

(a) Effective Date 

This AD is effective March 29, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–300, –400, and –500 

series airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracking in the center section of the 

horizontal stabilizer. We are issuing this AD 

to detect and correct cracking of the rear spar 

center section of the horizontal stabilizer that 

could lead to departure of the horizontal 

stabilizer from the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions for the Rear Spar Upper Chord 

Horizontal Flange of the Horizontal 

Stabilizer Center Section 

At the applicable times specified in table 

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

Alert Service Bulletin 737–55A1100, dated 

January 26, 2016, except as required by 

paragraphs (j)(1), (j)(2), and (j)(3) of this AD: 

Do the actions required by paragraph (g)(1) or 

(g)(2) of this AD; and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–55A1100, dated January 26, 2016, except 

as required by paragraph (j)(4) of this AD. Do 

all applicable related investigative and 

corrective actions at the applicable times 

specified in tables 5, 6, 7, and 8 of paragraph 

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

Bulletin 737–55A1100, dated January 26, 

2016. For airplanes on which ‘‘Option 1’’ of 

‘‘CONDITION 15: SURFACE HFEC 

INSPECTION OF THE CHORD AROUND 

THE GUSSETS—NO CRACK FOUND’’ is 

done as specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–55A1100, dated January 26, 2016, repeat 

the inspection specified in paragraph (g)(2) of 

this AD thereafter at the applicable times 

specified in table 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–55A1100, dated January 26, 

2016. 

(1) Do an inspection to identify the 

fasteners common to the rear spar upper 

chord upper gusset of the horizontal 

stabilizer center section. 

(2) Do a surface high frequency eddy 

current (HFEC) inspection of the rear spar 

upper chord around the two inboard gusset 

plates common to the thrust and auxiliary 

beams for any crack. 

(h) Repetitive Inspections of the Vertical 

Flange of the Rear Spar Upper Chord on the 

Horizontal Stabilizer Center Section 

At the applicable times specified in table 

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

Alert Service Bulletin 737–55A1100, dated 

January 26, 2016, except as required by 

paragraphs (j)(1) and (j)(2) of this AD: Do a 

surface HFEC inspection of the vertical flange 

of the rear spar upper chord; and do all 

applicable corrective actions; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–55A1100, 

dated January 26, 2016, except as required by 

paragraph (j)(4) of this AD. Do all applicable 

corrective actions before further flight. 

Repeat the inspection of the vertical flange of 

the rear spar upper chord thereafter at the 

time specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–55A1100, dated January 26, 

2016. 

(i) Repetitive Inspections of the Vertical 

Flange Stiffener Fasteners of the Rear Spar 

Upper Chord on the Horizontal Stabilizer 

Center Section 

At the applicable times specified in table 

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

Alert Service Bulletin 737–55A1100, dated 

January 26, 2016, except as required by 

paragraphs (j)(1) and (j)(2) of this AD: Do the 

actions required by paragraph (i)(1) or (i)(2) 

of this AD; and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–55A1100, dated January 26, 2016, except 

as required by paragraph (j)(4) of this AD. Do 

all applicable related investigative and 

corrective actions at the applicable times 

specified in tables 3 and 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–55A1100, dated January 26, 

2016. Repeat the inspection specified in 

paragraph (i)(2) of this AD thereafter at the 

applicable times specified in tables 3 and 4 

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

Alert Service Bulletin 737–55A1100, dated 

January 26, 2016. 

(1) Do an open hole HFEC inspection of the 

vertical flange at the stiffeners of the rear spar 

upper chord on the horizontal stabilizer 

center section for any crack. 

(2) Do a surface HFEC inspection of the 

vertical flange around the stiffeners of the 

rear spar upper chord on the horizontal 

stabilizer center section for any crack. 

(j) Exceptions to Service Information 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–55A1100, 

dated January 26, 2016, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–55A1100, 

dated January 26, 2016, refers to condition or 

compliance time in ‘‘horizontal stabilizer 

center section flight cycles’’ or ‘‘center 

section flight cycles,’’ this AD requires 


jstallworth on DSK7TPTVN1PROD with RULES
13274 Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations 

compliance for those conditions or 

compliance time in terms of airplane flight 

cycles. 

(3) The Condition column of table 1 in 

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

Alert Service Bulletin 737–55A1100, dated 

January 26, 2016, refers to ‘‘horizontal 

stabilizer center section flight cycles.’’ This 

AD, however, applies to the airplanes with 

the specified airplane total flight cycles as of 

the effective date of this AD. 

(4) Where Boeing Alert Service Bulletin 

737–55A1100, dated January 26, 2016; 

specifies to contact Boeing for appropriate 

action: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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. 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 (l) of this AD. Information may be 

emailed to 9-ANM-LAACO-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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (j)(4) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(l) Related Information 

For more information about this AD, 

contact Payman Soltani, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5313; fax: 562–627–5210; email: 

Payman.Soltani@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 737– 

55A1100, dated January 26, 2016. 

(ii) Reserved. 

(3) For Boeing 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. 

(4) You may view this 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 3, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–05515 Filed 3–11–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2016–0182] 

Drawbridge Operation Regulation; 

Willamette River, Portland, OR 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of deviation from 

drawbridge regulation. 

SUMMARY: The Coast Guard has issued a 

temporary deviation from the operating 

schedule that governs the Broadway 

Bridge across the Willamette River, mile 

11.7, at Portland, OR. The deviation is 

necessary to accommodate the Portland 

Race for the Roses event. This deviation 

allows the bridge to remain in the 

closed-to-navigation position to 

facilitate the safe movement of event 

participants across the bridge. 

DATES: This deviation is effective from 

5 a.m. to 10:30 a.m. on April 17, 2016. 

ADDRESSES: The docket for this 

deviation, [USCG–2016–0182] is 

available at http://www.regulations.gov. 

Type the docket number in the 

‘‘SEARCH’’ box and click ‘‘SEARCH.’’ 

Click on Open Docket Folder on the line 

associated with this deviation. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this temporary 

deviation, call or email Mr. Steven 

Fischer, Bridge Administrator, 

Thirteenth Coast Guard District; 

telephone 206–220–7282, email 

Steven.M.Fischer@uscg.mil. 

SUPPLEMENTARY INFORMATION: 

Multnomah County requested for the 

Broadway Bridge to remain closed to 

vessel traffic to facilitate the safe, 

uninterrupted roadway passage of 

participants in the Portland Race for the 

Roses event. The Broadway Bridge 

crosses the Willamette River at mile 

11.7, and provides 90 feet of vertical 

clearance above Columbia River Datum 

0.0 while in the closed-to-navigation 

position. This bridge operates in 

accordance with 33 CFR 117.897. This 

deviation allows the bascule span of the 

Broadway Bridge across the Willamette 

River, mile 11.7, to remain in the 

closed-to-navigation position, and need 

not open for maritime traffic from 5:00 

a.m. to 10:30 a.m. on April 17, 2016. 

The bridge shall operate in accordance 

to 33 CFR 117.897 at all other times. 

Waterway usage on this part of the 

Willamette River includes vessels 

ranging from commercial tug and barge 

to small pleasure craft. We have 

coordinated with the majority of 

waterway users and there were no 

objections to this schedule. 

Vessels able to pass through the 

bridge in the closed positions may do so 

at anytime. The bridge will be able to 

open for emergencies and there is no 

immediate alternate route for vessels to 

pass. The Coast Guard will also inform 

the users of the waterways through our 

Local and Broadcast Notices to Mariners 

of the change in operating schedule for 

the bridge so that vessels can arrange 

their transits to minimize any impact 

caused by the temporary deviation. 

In accordance with 33 CFR 117.35(e), 

the drawbridge must return to its regular 

operating schedule immediately at the 

end of the effective period of this 

temporary deviation. This deviation 

from the operating regulations is 

authorized under 33 CFR 117.35. 


jstallworth on DSK7TPTVN1PROD with RULES