292 Federal Register / Vol. 76, No. 2 / Tuesday, January 4, 2011 / Proposed Rules 

Although § 25.562 was written with 

forward- and aft-facing seats in mind, 

the orientation of the seat does not 

change the relevant test conditions, and 

the rule applies to all seats regardless of 

orientation. 

The dynamic test conditions included 

in § 25.562 are directly applicable to 

side-facing seats. However, for injury 

pass/fail criteria, the orientation of the 

seat may be significant. For forward-, 

aft-, and side-facing seats the injury 

criteria are currently limited to head, 

spine, and femur loads. The head and 

lumbar loads are critical but the femur 

load is not critical. For a side-facing 

seat, additional injury parameters may 

be identified and evaluation of those 

parameters would be necessary to 

provide an acceptable level of safety. 

When evaluating side-facing seats the 

following should be taken into 

consideration: 

1. The isolation of one occupant from 

another. Occupants should not rely on 

impact with other occupants to provide 

energy absorption; body-to-body 

impacts are unacceptable. 

2. The restraint system and the 

retention of occupants in the seat. 

Addressing this concern may necessitate 

providing a means of restraint for the 

lower limbs as well as the torso. Failure 

to limit the forward (in the airplane’s 

coordinate system) travel of the lower 

limbs may cause the occupant to come 

out of the restraint system or produce 

severe injuries due to the resulting 

position of the restraint system and/or 

twisting (torsional load) of the lower 

lumbar spinal column. 

3. The load limit in the torso in the 

lateral direction. Human tolerance for 

side-facing seats differs from that for 

forward- or aft-facing seats. 

The automotive industry has 

developed test procedures and occupant 

injury criteria appropriate for side 

impact conditions. The criteria include 

limiting lateral pelvic accelerations and 

using the ‘‘Thoracic Trauma Index,’’ 

which is defined in 49 CFR 571.214. 

Use of the side impact dummy (SID) 

identified in 49 CFR part 572, subpart 

F, rather than the Hybrid II dummy 

identified in 49 CFR part 572, subpart 

B, is required to evaluate these 

parameters. The Hybrid II dummy is 

used in the current § 25.562 test. Testing 

with a SID is the best means available 

to assess the injury potential of a 

sideward impact condition. Such an 

evaluation is considered necessary to 

provide an acceptable level of safety for 

side-facing seats. 

The side-facing seat proposed special 

conditions have been determined to 

result in a level of safety equivalent to 

that provided by the injury pass/fail 

criteria in § 25.562 for forward- or aftfacing seats. 

Applicability 

As discussed above, this proposed 

special condition is applicable to the 

GVI. Should Gulfstream apply at a later 

date for a change to the type certificate 

to include another model incorporating 

the same novel or unusual design 

features, this proposed special condition 

would apply to that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features of the GVI. It 

is not a rule of general applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

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

44702, 44704. 

The Proposed Special Conditions 

Accordingly, the Federal Aviation 

Administration (FAA) proposes the 

following special conditions as part of 

the type certification basis for the GVI 

airplanes. 

In addition to the airworthiness 

standards in §§ 25.562 and 25.785, the 

following proposed special conditions 

provide injury criteria and installation/ 

testing guidelines that represent the 

minimum acceptable airworthiness 

standard for single-place side-facing 

seats: 

A. The Proposed Injury Criteria 

1. Existing Criteria: All injury 

protection criteria of § 25.562(c)(1) 

through (c)(6) apply to the occupant of 

a side-facing seat. Head injury criterion 

(HIC) assessments are only required for 

head contact with the seat and/or 

adjacent structures. 

2. Body-to-Wall/Furnishing Contact: 

The seat must be installed aft of a 

structure such as an interior wall or 

furnishing that will support the pelvis, 

upper arm, chest, and head of an 

occupant seated next to the structure. A 

conservative representation of the 

structure and its stiffness must be 

included in the tests. It is 

recommended, but not required, that the 

contact surface of this structure be 

covered with at least two inches of 

energy absorbing protective padding 

(foam or equivalent), such as Ensolite. 

3. Thoracic Trauma: Thoracic trauma 

index (TTI) injury criterion must be 

substantiated by dynamic test or by 

rational analysis based on previous 

test(s) of a similar seat installation. 

Testing must be conducted with a side 

impact dummy (SID), as defined by 

Title 49, Code of Federal Regulations 

(49 CFR) part 572, Subpart F, or its 

equivalent. TTI must be less than 85, as 

defined in 49 CFR part 572, subpart F. 

SID TTI data must be processed as 

defined in Federal Motor Vehicle Safety 

Standard (FMVSS) part 571.214, section 

S6.13.5. 

4. Pelvis: Pelvic lateral acceleration 

must be shown by dynamic test or by 

rational analysis based on previous 

test(s) of a similar seat installation not 

to exceed 130g. Pelvic acceleration data 

must be processed as defined in FMVSS 

part 571.214, section S6.13.5. 

5. Shoulder Strap Loads: Where upper 

torso straps (shoulder straps) are used 

for occupants, tension loads in 

individual straps must not exceed 1,750 

pounds. If dual straps are used for 

restraining the upper torso, the total 

strap tension loads must not exceed 

2,000 pounds. 

B. General Test Guidelines 

1. One longitudinal test with the SID 

or its equivalent, undeformed floor, no 

yaw, and with all lateral structural 

supports (armrests/walls). 

Pass/fail injury assessments: TTI and 

pelvic acceleration. 

2. One longitudinal test with the 

Hybrid II anthropomorphic test dummy 

(ATD), deformed floor, with 10 degrees 

yaw, and with all lateral structural 

support (armrests/walls). 

Pass/fail injury assessments: HIC; and 

upper torso restrain load, restraint 

system retention and pelvic 

acceleration. 

3. Vertical (14g) test is to be 

conducted with modified Hybrid II 

ATDs with existing pass/fail criteria. 

Issued in Renton, Washington, on 

December 22, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33221 Filed 1–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24145; Directorate 

Identifier 2006–NE–06–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF6–45 and CF6–50 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Federal Register / Vol. 76, No. 2 / Tuesday, January 4, 2011 / Proposed Rules 293 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to General Electric 

Company (GE) CF6–45 and CF6–50 

series turbofan engines. The existing AD 

requires replacing certain forward and 

aft centerbodies of the long fixed core 

exhaust nozzle (LFCEN) assembly. Since 

we issued that AD, we became aware 

that other forward and aft centerbodies 

are also affected. This proposed AD 

would add certain new centerbodies 

requiring replacement. This proposed 

AD is prompted by the discovery of 

more part numbers (P/Ns) of 

centerbodies requiring replacement. We 

are proposing this AD to prevent the 

forward and aft centerbody of the 

LFCEN assembly from separating from 

the engine, damage to the engine, and 

damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by February 18, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: 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 General Electric 

Company, GE–Aviation, Room 285, 1 

Neumann Way, Cincinnati, OH 45215, 

telephone 513–552–3272; fax 513–552– 

3329; e-mail: geae.aoc@ge.com. You 

may review copies of the referenced 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Tomasz Rakowski, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate; phone: 781– 

238–7735; fax: 781–238–7199; e-mail: 

tomasz.rakowski@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–2006–24145; Directorate Identifier 

2006–NE–06–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 February 12, 2009, we issued AD 

2009–04–17, Amendment 39–15823 (74 

FR 8735, February 26, 2009), for GE 

CF6–45 and CF6–50 series turbofan 

engines. That AD requires replacing 

LFCEN assembly forward centerbodies 

P/N 1313M55G01 or G02, P/N 

9076M28G09 or G10, and aft 

centerbodies P/N 1313M56G01 or 

9076M46G05 with modified 

centerbodies. That AD resulted from 

reports of separation of centerbodies 

from the engine due to high imbalance 

engine conditions caused by events 

including bird strikes. Separation of the 

centerbodies from the engine would 

cause engine damage and airplane 

damage. We issued that AD to prevent 

the forward and aft centerbody of the 

LFCEN assembly from separating from 

the engine, damage to the engine, and 

damage to the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2009–04–17, we 

identified seven additional centerbody 

P/Ns that should have been included in 

the AD. These centerbodies are of the 

same design and construction as those 

identified in the original AD and 

therefore, are subject to the same unsafe 

condition. We added forward 

centerbodies P/N 9076M28G05, G06, 

G08, P/N 9076M82G01, G03, and aft 

centerbodies P/N 9076M46G02, G04 to 

the applicability of this proposed AD to 

remove them from service. 

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 add forward 

centerbody P/Ns 9076M28G05, G06, and 

G08, P/Ns 9076M82G01, G03, and aft 

centerbody P/Ns 9076M46G02, G04, to 

those P/Ns in AD 2009–04–17 to be 

removed from service. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 383 GE CF6–45 and CF6– 

50 series turbofan engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 44 

work hours per engine to perform the 

actions required by this AD, and that the 

average labor rate is $85 per work-hour. 

Required parts would cost about 

$11,000 per engine. Based on these 

figures, we estimate the total cost of this 

AD to U.S. operators to be $5,645,420. 

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. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
294 Federal Register / Vol. 76, No. 2 / Tuesday, January 4, 2011 / Proposed Rules 

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, 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) 

2009–04–17, Amendment 39–15823 (74 

FR 8735; February 26, 2009), and adding 

the following new AD: 

General Electric Company: Docket No. FAA– 

2006–24145; Directorate Identifier 2006– 

NE–06–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by February 18, 2011. 

Affected ADs 

(b) This AD supersedes AD 2009–04–17, 

Amendment 39–15823. 

Applicability 

(c) This AD applies to the following 

engines with a long fixed core exhaust nozzle 

(LFCEN) assembly forward centerbody, part 

number (P/N) 1313M55G01 or G02, P/N 

9076M28G05, G06, G08, G09, or G10, P/N 

9076M82G01 or G03, and aft centerbody 

P/N 1313M56G01, or P/N 9076M46G02, G04, 

or G05, installed in: 

(1) General Electric Company (GE) CF6– 

45A, CF6–45A2, CF6–50A, CF6–50C, CF6– 

50CA, CF6–50C1, CF6–50C2, CF6–50C2B, 

CF6–50C2D, CF6–50E, CF6–50E1, CF6–50E2, 

and CF6–50E2B turbofan engines; including 

engines marked on the engine data plate as 

CF6–50C2–F and CF6–50C2–R. 

(2) These engines are installed on, but not 

limited to, Airbus A300 series, Boeing 747 

series, McDonnell Douglas DC–10 series, and 

DC–10–30F (KDC–10) airplanes. 

Unsafe Condition 

(d) This AD was prompted by the 

discovery of more P/Ns of centerbodies 

affected, requiring replacement. We are 

issuing this AD to prevent the forward and 

aft centerbody of the LFCEN assembly from 

separating from the engine, damage to the 

engine, and damage to the airplane. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 18 months after the effective 

date of this AD, replace forward centerbody, 

P/N 1313M55G01 and G02, P/N 

9076M28G05, G06, G08, G09, and G10, P/N 

9076M82G01 and G03, and aft centerbody 

P/N 1313M56G01, P/N 9076M46G02, G04, 

and G05 with a forward and aft centerbody 

that has been modified using the 

Accomplishment Instructions, Section 3, of 

GE Service Bulletin (SB) No. CF6–50 S/B 78– 

0244, Revision 1, dated March 13, 2008, 

CF6–50 S/B 78–0244, dated July 30, 2007, or 

CF6–50 S/B 78–0242, dated September 26, 

2005. 

Centerbody Installation Prohibition 

(2) After 18 months from the effective date 

of this AD, do not install any engine with 

forward centerbody, P/N 1313M55G01 or 

G02, P/N 9076M28G05, G06, G08, G09, or 

G10, P/N 9076M82G01 or G03, or aft 

centerbody P/N 1313M56G01, P/N 

9076M46G02, G04, or G05 on any airplane. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Engine Certification 

Office, FAA, may approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(g) For more information about this AD, 

contact Tomasz Rakowski, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate; phone: 781– 

238–7735; fax: 781–238–7199; e-mail: 

tomasz.rakowski@faa.gov. 

(h) For service information identified in 

this AD, contact General Electric Company, 

GE–Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215, telephone 513–552– 

3272; fax 513–552–3329; e-mail: 

geae.aoc@ge.com. You may review copies of 

the referenced service information at the 

FAA, Engine & Propeller Directorate. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

December 28, 2010. 

Peter A. White, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33167 Filed 1–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

National Oceanic and Atmospheric 

Administration 

15 CFR Part 922 

[0908041219–0073–02] 

RIN 0648–AX79 

Amendments to National Marine 

Sanctuary Regulations Regarding Low 

Overflights in Designated Zones 

AGENCY: Office of National Marine 

Sanctuaries (ONMS), National Oceanic 

and Atmospheric Administration 

(NOAA), Department of Commerce 

(DOC). 

ACTION: Extension of public comment 

period. 

SUMMARY: On December 8, 2010, NOAA 

published a proposed rule in the 

Federal Register to amend the low 

overflight regulations of the Channel 

Islands, Monterey Bay, Gulf of the 

Farallones, and Olympic Coast national 

marine sanctuaries. Specifically, NOAA 

proposes to amend the regulations 

requiring that motorized aircraft 

maintain certain minimum altitudes 

above specified locations within the 

boundaries of the listed sanctuaries; and 

state that failure to comply with these 

altitude limits is presumed to disturb 

marine mammals or seabirds and is a 

violation of the sanctuary regulations. 

DATES: The public comment period on 

the proposed rule published at 75 FR 

76319, December 8, 2010, will be 

extended an additional 30 days from the 

original due date of January 7, 2011. 

Comments will be accepted through 

February 7, 2011. 

ADDRESSES: You may submit comments, 

identified by RIN 0648–AX79 by any 

one of the following methods: 

• Electronic Submissions: Submit all 

electronic public comments via the 

Federal eRulemaking Portal http:// 

www.regulations.gov. 

• Mail: Debra Malek, Office of 

National Marine Sanctuaries, 1305 EastWest Highway, 11th floor, Silver Spring, 

MD 20910. 

Instructions: No comments will be 

posted for public viewing until after the 

comment period has closed. All 

comments received are a part of the 

public record and will be posted to 

http://www.regulations.gov without 

change. All Personal Identifying 

Information (for example, name, 

address, etc.) voluntarily submitted by 

the commenter may be publicly 

accessible. Do not submit confidential 

business information or otherwise 

sensitive or protected information. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1