59790 Federal Register / Vol. 69, No. 193 / Wednesday, October 6, 2004 / Rules and Regulations 

corrosion pitting or cracking, replace the 

cable assembly with an airworthy cable 

assembly before further flight. Replacing the 

cable assembly with an airworthy cable 

assembly is terminating action for the 

requirements of this AD. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Los Angeles Aircraft 

Certification Office, FAA, for information 

about previously approved alternative 

methods of compliance. 

(c) Do the inspection by following MD 

Helicopters, Inc. Service Bulletin SB500N–

027, SB600N–042, dated May 3, 2004. The 

Director of the Federal Register approved this 

incorporation by reference in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Copies may be obtained from MD Helicopters 

Inc., Attn: Customer Support Division, 4555 

E. McDowell Rd., Mail Stop M615–GO48, 

Mesa, Arizona 85215–9734, telephone 1–

800–388–3378, fax 480–891–6782, or on the 

Web at http://www.mdhelicopters.com.

Copies may be inspected 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/code_of_federal_regulations/

ibr_locations.html.

(d) This amendment becomes effective on 

October 21, 2004.

Issued in Fort Worth, Texas, on September 

22, 2004. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service.

[FR Doc. 04–22264 Filed 10–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19229; Directorate 

Identifier 2004–NM–195–AD; Amendment 

39–13814; AD 2004–20–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD requires repetitive 

inspections for cracks, sealant damage, 

and corrosion of the main fittings of the 

main landing gear (MLG), and corrective 

actions if necessary. This AD is 

prompted by a report of a cracked main 

fitting of the MLG. We are issuing this 

AD to detect and correct fatigue 

cracking of the main fitting of the MLG 

and consequent failure of the main 

fitting, which could result in the 

collapse of the MLG.

DATES: Effective October 21, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of October 21, 2004. 

We must receive comments on this 

AD by December 6, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to http:/

/dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Bombardier, Inc., 

Canadair, Aerospace Group, P.O. Box 

6087, Station Centre-ville, Montreal, 

Quebec H3C 3G9, Canada. You can 

examine this information 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/

code_of_federal_regulations/

ibr_locations.html.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Examining the Docket 

You can examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Serge 

Napoleon, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7312; fax 

(516) 794–5531. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: Transport 

Canada Civil Aviation (TCCA), which is 

the airworthiness authority for Canada, 

notified the FAA that an unsafe 

condition may exist on certain 

Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. TCCA advises that it has 

received a report of a cracked main 

fitting of the main landing gear (MLG) 

at the section between the forward face 

of the main fitting on the trunnion side 

and the area just above the upper attach 

lug radius of the shock strut. Laboratory 

examination has found that the fatigue 

crack was initiated from a corrosion pit 

located on the chamfer of the inner bore 

of the pintle pin socket of the main 

fitting of the MLG. This condition, if not 

detected and corrected in a timely 

manner, could cause failure of the main 

fitting of the MLG, which could result 

in the collapse of the MLG.

Relevant Service Information 

Bombardier has issued Alert Service 

Bulletin A601R–32–099, including 

Appendices A through D, dated 

September 15, 2004. The service 

bulletin describes the following 

procedures: 

• Repetitive detailed inspections for 

cracks of the inboard and outboard sides

Federal Register / Vol. 69, No. 193 / Wednesday, October 6, 2004 / Rules and Regulations 59791

of the main fitting of the MLG between 

the pintle pin trunnion and the radius 

of the shock strut lug; 

• Repetitive detailed inspections for 

sealant damage or corrosion around the 

forward bushing of the left and right 

main fittings of the MLG; 

• Repetitive ultrasonic inspections for 

cracks of the left and right main fittings 

of MLG; and 

• Corrective actions if necessary. The 

corrective actions include replacing any 

cracked main fitting of the MLG with a 

new or serviceable main fitting; doing 

an eddy current inspection to verify that 

there is a crack on the fitting if 

necessary; and repeating certain 

inspections described previously at 

reduced intervals; as applicable. 

TCCA mandated the service bulletin 

and issued Canadian airworthiness 

directive CF–2004–18, dated September 

16, 2004, to ensure the continued 

airworthiness of these airplanes in 

Canada. 

FAA’s Determination and Requirements 

of This AD 

This airplane model is manufactured 

in Canada and is type certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. Pursuant to 

this bilateral airworthiness agreement, 

TCAA has kept the FAA informed of the 

situation described above. We have 

examined TCCA’s findings, evaluated 

all pertinent information, and 

determined that we need to issue an AD 

for products of this type design that are 

certificated for operation in the United 

States. 

Therefore, we are issuing this AD to 

detect and correct fatigue cracking of the 

main fitting of the MLG and consequent 

failure of the main fitting, which could 

result in the collapse of the MLG. This 

AD requires accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the AD and Referenced Service Bulletin/

Canadian Airworthiness Directive.’’

Differences Between the AD and 

Referenced Service Bulletin/Canadian 

Airworthiness Directive 

Operators should note that, although 

the Accomplishment Instructions of the 

referenced service bulletin describe 

procedures for reporting crack 

indications, returning cracked parts to 

Messier Dowty, and submitting a 

comment sheet related to service 

bulletin quality and a sheet recording 

compliance with the service bulletin, 

this AD, like Canadian airworthiness 

directive CF–2004–18, will not require 

those actions. We do not need this 

information from operators. 

In addition, if there is evidence of 

sealant damage or corrosion, the 

referenced service bulletin describes 

procedures for accomplishing only the 

ultrasonic inspection at intervals not to 

exceed 500 flight cycles. This AD, as 

well as the Canadian airworthiness 

directive, requires repeating the detailed 

inspection of the main fitting lateral 

surface within 5 days following the 

visual inspection of the sealant, and 

every 5 days thereafter, in addition to 

the ultrasonic inspections of the main 

fittings within 500 flight cycles. 

Canadian airworthiness directive CF–

2004–18 specifies that the required 

actions must be done in accordance 

with Bombardier Alert Service Bulletin 

A601R–32–099, dated September 15, 

2004, or ‘‘later revisions approved by 

the Chief, Continuing Airworthiness, 

Aircraft Certification, Transport 

Canada.’’ We cannot use the phrase, ‘‘or 

later FAA-approved revisions,’’ in an 

AD when referring to the service 

document because doing so violates 

Office of the Federal Register (OFR) 

regulations for approval of materials 

‘‘incorporated by reference’’ in rules. In 

general terms, we are required by these 

OFR regulations to either publish the 

service document contents as part of the 

actual AD language; or submit the 

service document to the OFR for 

approval as ‘‘referenced’’ material, in 

which case we may only refer to such 

material in the text of an AD. The AD 

may refer to the service document only 

if the OFR approved it for 

‘‘incorporation by reference.’’ To allow 

operators to use later revisions of the 

referenced document (issued after 

publication of the AD), either we must 

revise the AD to reference specific later 

revisions, or operators must request 

approval to use later revisions as an 

alternative method of compliance with 

this AD under the provisions of 

paragraph (m) of this AD. 

Interim Action 

This is considered to be interim 

action until final action is identified, at 

which time we may consider further 

rulemaking. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19229; Directorate Identifier 

2004–NM–195–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket web site, 

anyone can find and read the comments 

in any of our dockets, including the 

name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You can review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you can visit 

http://dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications with 

you. You can get more information 

about plain language at http://www/

faa.gov/language and http://

www.plainlanguage.gov.

Regulatory Findings 

We have determined that 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 the 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

59792 Federal Register / Vol. 69, No. 193 / Wednesday, October 6, 2004 / Rules and Regulations 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation.

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):

2004–20–09 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–13814. 

Docket No. FAA–2004–19229; 

Directorate Identifier 2004–NM–195–AD. 

Effective Date 

(a) This AD becomes effective October 21, 

2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, serial numbers 7003 through 7067 

inclusive and 7069 through 8999 inclusive, 

certificated in any category; equipped with 

main landing gear (MLG) main fittings, part 

number (P/N) 601R85001–3 or –4 (Messier 

Dowty P/N 17064–101, –102, –103, or –104). 

Unsafe Condition 

(d) This AD was prompted by a report of 

a cracked main fitting of the MLG. The FAA 

is issuing this AD to detect and correct 

fatigue cracking of the main fitting of the 

MLG and consequent failure of the main 

fitting, which could result in the collapse of 

the MLG. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Service Bulletin 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A601R–32–099, including 

Appendices A, B, and D, and excluding 

Appendix C, dated September 15, 2004. 

Initial Inspections 

(g) Do the actions specified in Table 1 of 

this AD.

TABLE 1.—INITIAL INSPECTIONS

Do— At the latest of—

(1) A detailed inspection for cracks of the inboard and outboard sides of the main fitting of the 

MLG between the pintle pin trunnion and the radius of the shock strut lug, in accordance 

with Part A of the service bulletin.

(i) Before the accumulation of 8,000 total flight 

cycles since the main fitting of the MLG was 

new. 

(ii) Within 8,000 flight cycles since the last 

overhaul of the MLG. 

(iii) Within 50 flight cycles after the effective 

date of this AD. 

(2) A detailed inspection for sealant damage or corrosion around the forward bushing of the left 

and right main fittings of the MLG, in accordance with Part B of the service bulletin.

(i) Before the accumulation of 8,000 total flight 

cycles since the main fitting of the MLG was 

new. 

(ii) Within 8,000 flight cycles since the last 

overhaul of the MLG. 

(iii) Within 500 flight cycles after the effective 

date of this AD. 

(3) An ultrasonic inspection for cracks of the left and right main fittings of the MLG, in accordance with Part C of the service bulletin.(i) Before the accumulation of 8,000 total flight 

cycles since the main fitting of the MLG was 

new. 

(ii) Within 8,000 flight cycles since the last 

overhaul of the MLG. 

(iii) Within 500 flight cycles after the effective 

date of this AD. 

Note 1: For the purposes of this AD, a 

detailed inspection is ‘‘an intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirrors magnifying 

lenses, etc. may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Repetitive Inspections 

(h) Repeat the inspections required by 

paragraph (g) of this AD at the time specified 

in Table 2 of this AD.

TABLE 2.—REPETITIVE INSPECTION INTERVAL

For the inspection required by— Repeat at intervals not to exceed— Until the action required by—

(1) Paragraph (g)(1) of this AD ......................................... 5 days ....................................................... Paragraph (g)(3) of the AD is done, unless required by paragraph (j) of this 

AD. 

(2) Paragraph (g)(2) of this AD ......................................... 500 flight cycles ........................................ Paragraph (j)(2) of this AD is done. 

(3) Paragraph (g)(3) of this AD ......................................... 5,000 flight cycles, except as required by 

paragraph (j)(2) of this AD.

(None). 

Federal Register / Vol. 69, No. 193 / Wednesday, October 6, 2004 / Rules and Regulations 59793

Corrective Actions 

(i) If there is an indication of a crack during 

any inspection required by paragraph (g)(1), 

(h)(1), or (j)(1) of this AD, before further 

flight, do the actions specified in paragraphs 

(i)(1) or (i)(2) of this AD in accordance with 

Part A of the service bulletin. 

(1) Replace the cracked main fitting of the 

MLG with a new or serviceable main fitting. 

(2) Do an eddy current inspection to verify 

whether there is a crack. If there is a crack, 

replace the cracked main fitting of the MLG 

with a new or serviceable main fitting. 

(j) If any sealant damage or corrosion is 

found during any inspection required by 

either paragraph (g)(2) or (h)(2) of this AD, do 

the actions specified in Table 3 of this AD 

in accordance with Part B of the service 

bulletin.

TABLE 3.—CORRECTIVE ACTIONS FOR SEALANT DAMAGE OR CORROSION

Do the inspection specified in— Within— Repeat at intervals not to

exceed— Until the action specified in—

(1) Paragraph (g)(1) of this AD .................. 5 days after doing the inspection required by paragraph 

(g)(2) or (h)(2) of this AD, as 

aplicable.

5 days ....................................... Paragraph (j)(2) of this AD is 

done. 

(2) Paragraph (g)(3) of this AD .................. 500 flight cycles after doing the 

inspection required by paragraph (g)(2) or (h)(2) of this 

AD, as applicable.

500 flight cycles ........................ (None). 

(k) If there is an indication of a crack 

during any inspection required by paragraph 

(g)(3), (h)(3), or (j)(2) of this AD, before 

further flight, replace the cracked main fitting 

of the MLG with a new or serviceable main 

fitting in accordance with Part C of the 

service bulletin. 

No Reporting or Returning of Parts 

(l) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the airplane manufacturer and 

to return cracked main fittings to the 

supplier, this AD does not include those 

requirements. 

Alternative Methods of Compliance 

(AMOCs) 

(m) The Manager, New York Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

Related Information 

(n) Canadian airworthiness directive CF–

2004–18, dated September 16, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(o) You must use Bombardier Alert Service 

Bulletin A601R–32–099, including 

Appendices A, B, and D, and excluding 

Appendix C, dated September 15, 2004, to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approves the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. For copies of the service information, 

contact Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, Station 

Centre-ville, Montreal, Quebec H3C 3G9, 

Canada. You can review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW, room 

PL–401, Nassif Building, Washington, DC; or 

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/code_of_

federal_regulations/ibr_locations.html.

Issued in Renton, Washington, on 

September 27, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service

[FR Doc. 04–22266 Filed 10–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 100 

[CGD05–04–190] 

RIN 1625–AA08 

Special Local Regulations for Marine 

Events; John H. Kerr Reservoir, 

Clarksville, VA

AGENCY: Coast Guard, DHS.

ACTION: Temporary final rule.

SUMMARY: The Coast Guard is 

establishing temporary special local 

regulations for ‘‘Clarksville Hydroplane 

Challenge’’, a power boat race to be held 

over the waters of the John H. Kerr 

Reservoir adjacent to Clarksville, 

Virginia. These special local regulations 

are necessary to provide for the safety of 

life on navigable waters during the 

event. This action is intended to restrict 

vessel traffic in portions of the John H. 

Kerr Reservoir adjacent to Clarksville, 

Virginia during the power boat race.

DATES: This rule is effective from 11:30 

a.m. on October 9, 2004, to 5:30 p.m. on 

October 10, 2004.

ADDRESSES: Documents indicated in this 

preamble as being available in the 

docket are part of docket CGD05–04–

190 and are available for inspection or 

copying at Commander (oax), Fifth 

Coast Guard District, 431 Crawford 

Street, Portsmouth, Virginia 23704–

5004, between 9 a.m. and 2 p.m., 

Monday through Friday, except Federal 

holidays.

FOR FURTHER INFORMATION CONTACT: D. 

M. Sens, Project Manager, Auxiliary and 

Recreational Boating Safety Branch, at 

(757) 398–6204.

SUPPLEMENTARY INFORMATION:

Regulatory Information 

We did not publish a notice of 

proposed rulemaking (NPRM) for this 

regulation. Under 5 U.S.C. 553(b)(B), the 

Coast Guard finds that good cause exists 

for not publishing an NPRM. Publishing 

an NPRM would be impracticable, and 

contrary to public interest, as the event 

will take place before the NPRM process 

can be completed. Immediate action is 

needed to protect the safety of life at sea 

from the danger posed by high-speed 

power boats. Under 5 U.S.C. 553(d)(3), the Coast 

Guard finds that good cause exists for 

making this rule effective less than 30 

days after publication in the Federal 

Register. Delaying the effective date 

would be contrary to the public interest, 

since immediate action is needed to 

ensure the safety of the event 

participants, spectator craft and other 

vessels transiting the event area. 

However advance notifications will be 

made to affected waterway users via 

marine information broadcasts and area 

newspapers. 

Background and Purpose 

On October 9 and 10, 2004, the 

Virginia Boat Racing Association will 

sponsor the ‘‘Clarksville Hydroplane 

Challenge’’, on the waters of the John H. 

Kerr Reservoir. The event will consist of 

approximately 60 inboard hydroplanes 

racing in heats counter-clockwise 

around an oval racecourse. A fleet of 

spectator vessels is expected to gather 

nearby to view the competition. Due to 

the need for vessel control during the