## 24835 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations

instructions in Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).

(2) Revise the Limitations section of the applicable AFM to prohibit the in-flight use of the green EMPs. This may be accomplished by inserting a copy of this AD into the Limitations section of the AFM.
(h) Inspecting for Damage and Chafing

Within 500 flight hours or 4 months after the effective date of this AD, whichever occurs first, do a one-time general visual inspection for correct condition (i.e., no damage and no chafing) and correct installation of the hydraulic pressure hoses, electrical conduits, feeder cables, and associated clamping devices at frame 54, as well as the electrical conduits and feeder cables underneath the clamps (including removal of the concerned clamps), in accordance with the instructions in Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs). If any incorrect installation is found, before further flight, install the affected parts correctly, in accordance with Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).

(1) If any damage or chafing marks are found during the inspection required by paragraph (h) of this AD, before further flight, replace or repair the affected parts (hydraulic pressure hoses, electrical conduits, feeder cables, clamps, and spacer, if installed), in accordance with the instructions in Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).

(2) Before further flight after compliance with the requirements of paragraph (h) of this AD, as applicable, remove the placard required by paragraph (g)(1) of this AD; and remove the revision of the Limitations section of the AFM, as required by paragraph (g)(2) of this AD; from the airplane and the AFM, respectively.

(i) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; 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.
(j) Related Information

Refer to MCAI EASA Airworthiness Directive 2011–0071, dated April 18, 2011; Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011; and Airbus All Operators Telex A310–29A2102, dated April 12, 2011; for related information.
(k) Material Incorporated by Reference

(1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51:

(i) Airbus All Operators Telex A310– 29A2101, Revision 01, dated April 12, 2011. The document number, revision level, and issue date of this document is specified only on the first page of the document.

(ii) Airbus All Operators Telex A310– 29A2102, dated April 12, 2011. The document number, revision level, and issue date of this document is specified only on the first page of the document.

(2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email: account.airwortheas@airbus.com; Internet http:// www.airbus.com.

(3) You may review copies of the 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.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_ register/code

_ of

_ federal

_ regulations/ ibr

_ locations.html. Issued in Renton, Washington, on April 12,

2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–9475 Filed 4–25–12; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0277; Directorate Identifier 2009–NM–217–AD; Amendment**  **39–17031; AD 2012–08–14]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracking in the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar, which could result in the loss of the strut-to-wing upper link load path and possible separation of a strut and engine from the airplane during flight. This AD requires repetitive inspections to detect fatigue cracking in the wing skin, and corrective actions if necessary. We are issuing this AD to correct the unsafe condition on these products.

**DATES** 

### : This AD is effective May 31,

2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 31, 2012.

**ADDRESSES** 

### : 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://


## 24836 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations

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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT** 

### : Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6577; fax: 425–917–6590; email: berhane.alazar@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That SNPRM was published in the Federal Register on October 11, 2011 (76 FR 62663). The original NPRM (75 FR 15357, March 29, 2010) proposed to require repetitive inspections to detect fatigue cracking in the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar, and corrective actions if necessary. The SNPRM proposed to revise that NPRM by reducing compliance times.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM (76 FR 62663, October 11, 2011) and the FAA’s response to each comment.
Supportive Comment

Boeing concurs with the contents of the SNPRM (76 FR 62663, October 11, 2011). Request for Relief From Alternative Methods of Compliance (AMOC) Requirement

Aviation Partners Boeing (APB) requested that we revise the SNPRM (76 FR 62663, October 11, 2011) to state that supplemental type certificate (STC) ST01920SE ( http://rgl.faa.gov/ Regulatory

_ and

_ Guidance

_Library/ rgstc.nsf/0/082838ee177dbf6286257 6a4005cdfc0/$FILE/ST01920SE.pdf ), has no impact on the inspection intervals and corrective actions. APB stated that structural analysis shows that the inspection intervals and required corrective actions in the SNPRM are unaffected by the installation of the APB winglets; therefore, there is no need for an AMOC.

We agree with the request. We must receive a request for approval of an AMOC, as required by 14 CFR 39.17 (Section 39.17 of the Federal Aviation Regulations), if a change in a product affects the ability to accomplish the actions required by the AD. We agree that the referenced STC does not affect accomplishment of the requirements of this AD, and an AMOC is not necessary for a ‘‘change in product’’ AMOC approval request. We have therefore added this provision in new Note 1 to paragraph (c) of this AD. Request To Revise Paragraph (g) of the SNPRM (76 FR 62663, October 11, 2011)

Delta requested that we revise paragraph (g) of the SNPRM (76 FR 62663, October 11, 2011) to include the following statement:

If, during opening for access to perform Part 2 inspection [of the Accomplishment Instructions of Boeing Alert Service Bulletin 767–57A0117, Revision 1, dated March 2, 2011], a freeze plug is found in the upper skin at any fastener location included in the service bulletin, then the inspections per Part 2 must be discontinued, and Part 1 inspections must be used for that wing for that visit and for all subsequent repeat inspections. 

### Delta stated that since open-hole eddy current inspections of any freeze plug would not detect cracks, the requirement to use Part 2 inspections should not be applied to any freeze plug including previously accomplished repairs.

Although we agree with the commenter’s characterization of the requirements, we disagree that it is necessary to make this distinction in the AD. Boeing Alert Service Bulletin 767– 57A0117, Revision 1, dated March 2, 2011, clearly states which inspection must be done, but we have added ‘‘as applicable’’ in the first sentence of paragraph (g) of this AD, to clarify that only the actions that apply to the individual airplane are required.
Additional Changes to This Final Rule

We have revised the heading and wording for paragraph (i) of this AD. These changes do not affect the intent of this AD.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the SNPRM (76 FR 62663, October 11, 2011) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the SNPRM (76 FR 62663, October 11, 2011).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.
Costs of Compliance

We estimate that this AD affects 417 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

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

Inspection .......... 10 work-hours × $85 per hour = $850 per inspection cycle ........................ $28,836 $29,686 $12,379,062



### 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:


## 24837 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations

O N 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Hole repair ...................................... 1 work-hour per hole × maximum 48 holes per airplane × $85 per hour = up to $4,080 per airplane. $0 Up to $4,080.

Fastener replacement ..................... 1 work-hour per hole × maximum 48 holes per airplane × $85 per hour = up to $4,080 per airplane. 0 Up to $4,080.

Freeze plug repair .......................... 1 work-hour per hole × maximum 48 holes per airplane × $85 per hour = up to $4,080 per airplane. 0 Up to $4,080.



### 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):
2012–08–14 The Boeing Company: Amendment 39–17031; Docket No. FAA–2010–0277; Directorate Identifier
2009–NM–217–AD.

(a) Effective Date

This AD is effective May 31, 2012.

(b) Affected ADs

None.
(c) Applicability

This AD applies to The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 767–57A0117, Revision 1, dated March 2,

2011.

Note 1 to paragraph (c) of this AD: Supplemental Type Certificate (STC) ST01920SE ( http://rgl.faa.gov/ Regulatory

_ and

_ Guidance

_Library/rgstc.nsf/ 0/082838ee177dbf62862576a4005cdfc0/ $FILE/ST01920SE.pdf ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE 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 according to paragraph (j) of this AD.

(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

This AD was prompted by reports of cracking in the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar. We are issuing this AD to detect and correct fatigue cracking in the upper surface of the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar, which could result in the loss of the strut-to-wing upper link load path and possible separation of a strut and engine from the airplane during flight.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Initial and Repetitive Inspections

Except as provided by paragraph (h) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–57A0117, Revision 1, dated March 2, 2011: Do detailedand ultrasonic inspections, or do an openhole high-frequency eddy current inspection, as applicable, to detect cracking in the upper surface of the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–57A0117, Revision 1, dated March 2, 2011, except as required by paragraph (h) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspections thereafter at intervals not to exceed the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–57A0117, Revision 1, dated March 2, 2011.
(h) Exceptions to the Service Bulletin

(1) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 767–57A0117, Revision 1, dated March 2, 2011, specifies to contact Boeing for additional instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (j) of this AD.

(2) Where Boeing Alert Service Bulletin 767–57A0117, Revision 1, dated March 2, 2011, specifies a compliance time after the date of the original issue of Boeing Alert Service Bulletin 767–57A0117, dated October 1, 2009: This AD requires compliance within the specified compliance time after the effective date of this AD.

(i) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert


## 24838 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations

Service Bulletin 767–57A0117, dated October 1, 2009.
(j) Alternative Methods of Compliance (AMOCs)

(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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov

.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle Aircraft Certification Office (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.

(k) Related Information

For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: 425–917–6577; fax: 425–917– 6590; email: berhane.alazar@faa.gov. Or, email information to 9–ANM–Seattle-ACO– AMOC–Requests@faa.gov

. (l) Material Incorporated by Reference

(1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(i) Boeing Alert Service Bulletin 767– 57A0117, Revision 1, dated March 2, 2011.

(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.

(3) You may review copies of the 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.

(4) You may also review copies of the 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/ibr

_ locations.html. Issued in Renton, Washington, on April 11,

2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–9949 Filed 4–25–12; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF HOMELAND **SECURITY**

**Coast Guard**

**33 CFR Part 165**

**[Docket No. USCG–2012–0001]**

**RIN 1625–AA00**



### Safety Zone; Magothy River, Sillery **Bay, MD**

**AGENCY** 

### : Coast Guard, DHS.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : The Coast Guard is establishing a safety zone in certain waters of the Magothy River, in Sillery Bay, Maryland. This safety zone is necessary to provide for the safety of life, property and the environment. This safety zone restricts the movement of vessels throughout the regulated area during The Bumper Bash, held annually on the fourth Saturday of July.

**DATES** 

### : This rule is effective May 29,

2012.

**ADDRESSES** 

### : Comments and material received from the public, as well as documents mentioned in this preamble as being available in the docket, are part of docket USCG–2012–0001 and are available online by going to http:// www.regulations.gov, inserting USCG– 2012–0001 in the ‘‘Keyword’’ box, and then clicking ‘‘Search.’’ This material is also available for inspection or copying at the Docket Management Facility (M– 30), U.S. Department of Transportation, 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 FURTHER INFORMATION CONTACT** 

### : If you have questions on this rule, call or email Mr. Ronald Houck, Sector Baltimore Waterways Management Division, Coast Guard; telephone 410– 576–2674, email Ronald.L.Houck@uscg.mil . If you have questions on viewing the docket, call Renee V. Wright, Program Manager, Docket Operations, telephone 202–366–

9826.

**SUPPLEMENTARY INFORMATION** 

### : Regulatory Information On February 27, 2012, we published a notice of proposed rulemaking (NPRM) entitled ‘‘Safety Zone; Magothy River, Sillery Bay, MD’’ in the Federal Register (77 FR 11423). We received no comments on the proposed rule. No public meeting was requested, and none was held.
Basis and Purpose

Each year, on the fourth Saturday in July, hundreds of recreational boaters meet in Sillery Bay at Dobbins Island, Maryland for a gathering called ‘‘The Bumper Bash.’’ The activity began in 2007. Due to the growing presence of boaters in recent years, the annual gathering has become increasingly congested. In recent years, an estimated 700 recreational boats were anchored or moored alongside other boats (rafted). The crowds of persons on recreational vessels or other water craft create large lines of rafted boats filling in the beachfront area of Dobbins Island. The persons and vessels exceeded a safe limit. Accidental drownings, personnel injuries, boat fires, boat capsizings and sinkings, and boating collisions are safety concerns during such overcrowded events. Access on the water for emergency response to the beach area is critical. The Coast Guard has the authority to impose appropriate controls on activities that may pose a threat to persons, vessels and facilities under its jurisdiction. The Coast Guard sees the need for a permanent safety zone that will be enforced annually on the fourth Saturday in July, during a gathering of persons on recreational vessels and other water craft held in the Magothy River, in Sillery Bay, Maryland. The zone is needed to control movement within a waterway that is expected to be populated by persons and vessels seeking to attend The Bumper Bash activity.
Background

The Coast Guard anticipates a large recreational boating fleet in the Magothy River, in Sillery Bay, during The Bumper Bash at Dobbins Island, Maryland annually on the fourth Saturday in July. Due to the need to provide for the safety of persons and vessels within the regulated area vessel traffic will be restricted during the activity.

The purpose of this rule is to promote maritime safety, and to protect the environment and mariners transiting the area from the potential hazards associated with a large gathering of recreational vessels and other watercraft along a confined beachfront area with