11174 Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules 

that the number of times this rating can 

be used in one flight is not limited. 

Applicability 

As discussed above, these special 

conditions are applicable to PWC model 

PW210S turbo shaft engines. If Pratt and 

Whitney Canada applies later for a 

change to the type certificate to include 

another closely related model 

incorporating the same novel or unusual 

design feature, these special conditions 

would apply to that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of engine. It is not a rule of general 

applicability, and it affects only the 

applicant who applied to the FAA for 

approval of these features on the engine. 

List of Subjects in 14 CFR Part 33 

Air transportation, Aircraft, Aviation 

safety, Safety. 

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 Pratt and 

Whitney Canada (PWC) model PW210S 

turbo shaft engines. 

1. PART 1 DEFINITION. Unless 

otherwise approved by the 

Administrator and documented in the 

appropriate manuals and certification 

documents, the following definition 

applies to this special condition: ‘‘Rated 

30 Minute AEO Power’’, means the 

approved brake horsepower developed 

under static conditions at the specified 

altitude and temperature, and within 

the operating limitations established 

under part 33, and limited in use to 

periods not exceeding 30 minutes each. 

2. PART 33 REQUIREMENTS. 

(a) Sections 33.1 Applicability and 

33.3 General: As applicable, all 

documentation, testing and analysis 

required to comply with the part 33 

certification basis, must account for the 

30 minute AEO rating, limits and usage. 

(b) Section 33.4, Instructions for 

Continued Airworthiness (ICA). In 

addition to the requirements of § 33.4, 

the ICA must: 

(1) Include instructions to ensure that 

in-service engine deterioration due to 

rated 30 minute AEO power usage will 

not be excessive, meaning that all other 

approved ratings, including one engine 

inoperative (OEI), are available (within 

associated limits and assumed usage) for 

each flight; and that deterioration will 

not exceed that assumed for declaring a 

time between overhaul (TBO) period. 

(i) The applicant must validate the 

adequacy of the maintenance actions 

required under paragraph (b)(1) above. 

(2) Include in the airworthiness 

limitations section (ALS), any 

mandatory inspections and 

serviceability limits related to the use of 

the 30-minute AEO rating. 

(c) Section 33.87, Endurance Test. In 

addition to the requirements of 

§§ 33.87(a) and 33.87(d), the overall test 

run must include a minimum of 25 

hours of operation at 30 minute AEO 

power and limits, divided into periods 

of 30 minutes AEO power with alternate 

periods at maximum continuous power. 

(1) Each § 33.87(d) continuous oneengine-inoperative (OEI) rating test 

period of 30 minutes or longer, run at 

power and limits equal to or higher then 

the 30 minute AEO rating, may be 

credited toward this requirement. 

Issued in Burlington, Massachusetts on 

February 1, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–4570 Filed 2–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0099; Directorate 

Identifier 2010–SW–085–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S–76A, S– 

76B, and S–76C Helicopters Modified 

by Supplemental Type Certificate 

SR09211RC 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Sikorsky Aircraft Corporation (Sikorsky) 

S–76 model helicopters with a certain 

life raft deployment system (LRDS) 

installed per Supplemental Type 

Certificate (STC) SR09211RC. This 

proposed AD would require removing 

and replacing the pilot or co-pilot life 

raft deployment handle (handle) located 

on the left side of the ‘‘broom closet’’ of 

the helicopter. This proposed AD is 

prompted by an incident that occurred 

where the handle bent prior to the life 

raft deploying, and this prohibited the 

crew from successfully deploying and 

using the life raft. It was determined 

that the handle in this incident was not 

manufactured to the approved Type 

Design. We are proposing this AD to 

prevent the bending of the handle, 

which could result in failure of the life 

raft to deploy. This failure could lead to 

loss of access to the life raft after an 

emergency ditching on water. 

DATES: We must receive comments on 

this proposed AD by May 2, 2011. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• 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. 

You may get the service information 

identified in this proposed AD from 

Aero Seats and Systems, Inc., 340 

Thomas Place, Everman, Texas 76140, 

telephone (817) 551–0818, fax (817) 

551–0838, e-mail 

rcrouch@aeroseatsandsystems.com. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Martin Crane, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Rotorcraft 

Certification Office, 2601 Meacham 

Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5170, fax (817) 

222–5783. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0099, Directorate Identifier 

2010–SW–085–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules 11175 

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 

concerning this proposed AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Operations office 

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

through Friday, except Federal holidays. 

The Docket Operations office (telephone 

(800) 647–5527) is located in Room 

W12–140 on the ground floor of the 

West Building at the street address 

stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

Discussion 

We propose to adopt a new AD for the 

Sikorsky S–76A, S–76B, and S–76C 

model helicopters with an Aero Seats 

and Systems, Inc. (ASI) ASI–500 LRDS 

installed per STC SR09211RC. This 

proposed AD would require removing 

and replacing the handle located on the 

left side of the broom closet. This 

proposed AD is prompted by an 

incident that occurred in the United 

Kingdom (UK), and was reported under 

the UK Civil Aviation Authority’s 

Mandatory Occurrence Reporting 

System (MOR ref 200800658). 

Investigation of this incident 

determined that the handle bent prior to 

the life raft deploying, and this 

prohibited the crew from successfully 

deploying and using the life raft. It was 

determined that the installed handle 

was not manufactured to the approved 

Type Design, resulting in the handle 

being under-strength for its intended 

purpose. The installed handle was a 

tube handle welded to a machined cam. 

This condition, if not corrected, could 

result in failure of the life raft to deploy, 

which could lead to loss of access to the 

life raft after an emergency ditching on 

water. 

We have reviewed ASI’s Alert Service 

Bulletin No. 76–500–02, Revision C, 

dated September 16, 2010 (ASB), which 

describes procedures for removing the 

handle (tube handle welded to a 

machined cam), part number (P/N) ASI– 

700–45, and replacing it with the handle 

assembly, P/N ASI–700–49A, which is a 

one piece machined handle and cam, 

designed to provide more strength. 

We are proposing this AD because we 

have evaluated all the relevant 

information and determined the unsafe 

condition described previously is likely 

to exist or develop on other helicopters 

of the same type design. Therefore, this 

proposed AD would require the 

following actions within the next 100 

hours time-in-service (TIS), unless 

previously accomplished: 

• Install the safety pins, P/N ASI– 

625–14, to lock out the raft deployment 

pods. 

• Remove the pad, P/N BA7601. 

• Remove the top cover, P/N ASI– 

700–73. 

• Remove the cotter pin, P/N AN381– 

2–8, from the clevis pin, P/N MS 20392– 

2C9, located at the crew release handle 

assembly. 

• Remove the washer, P/N AN960– 

10L, and clevis pin from the cable, P/ 

N 2604750–90. 

• Disconnect the cable from the 

handle, P/N ASI–700–45, and secure the 

cable to the broom closet to prevent it 

from falling into the lower cover. 

• Remove the handle by removing the 

bolt, P/N AN4–11; nut, P/N MS20364– 

428A; and washers, P/N AN960–416L, 

from the raft deployment handle 

assembly (handle assembly), P/N ASI– 

700–41A. 

• Remove the safety pin, P/N ASI– 

700–80. 

• Remove and discard any ball 

bearings, and clean all surfaces of the 

remaining handle assembly. 

• Install the handle, P/N ASI–700– 

49A. 

• Reinstall the bolt, nut, and washers, 

P/N AN960–416L, and install the 

washer, P/N ASI–700–44, between the 

handle and the mount, P/N ASI–700–43, 

on the left side of the broom closet, and 

torque to 20 in-lb maximum. 

• Reinstall the safety pin. 

• Release the cable from the broom 

closet. 

• Reinstall the cable to the handle 

with the clevis pin. 

• Reinstall the washer, P/N AN960– 

10L, and the cotter pin on to the clevis 

pin. 

• Reinstall the top cover. 

• Reinstall the pad. 

• Remove the raft deployment pod 

lock out safety pins. 

These proposed actions are intended 

to prevent the handle from bending 

during raft deployment, which could 

lead to loss of access to the life raft after 

an emergency ditching on water. 

Differences Between This Proposed AD 

and Service Information 

This proposed AD differs from the 

manufacturer’s service bulletin by 

requiring compliance to the actions 

specified in this AD within 100 hours 

TIS, unless accomplished previously. 

The manufacturer’s service bulletin 

states that compliance must occur 

immediately upon receipt of a new 

design handle. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 65 helicopters on the U.S. 

registry. We estimate it will take about 

4 work-hours per helicopter to 

accomplish the proposed requirements. 

The average labor rate is $85 per workhour. In addition, we estimate the cost 

of the required parts to be $1,500 per 

helicopter. Based on these figures, we 

estimate the cost of the proposed AD to 

be approximately $1,840 per helicopter 

and $119,600 total cost for U.S. 

operators. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, this proposed AD 

would not have a substantial direct 

effect on the States, on the relationship 

between the national Government and 

the States, or on the distribution of 

power and responsibilities among the 

various levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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. 

We prepared a draft economic 

evaluation of the estimated costs to 

comply with this proposed AD. See the 

AD docket to examine the draft 

economic evaluation. 

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 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
11176 Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules 

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. 

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 adding 

the following new AD: 

Sikorsky Aircraft Corporation: Docket No. 

FAA–2011–0099; Directorate Identifier 

2010–SW–085–AD. 

Applicability: S–76A, S–76B, and S–76C 

model helicopters with Aero Seats and 

Systems, Inc. (ASI) ASI–500 Life Raft 

Deployment System (LRDS) installed per 

FAA Supplemental Type Certificate 

SR09211RC, pilot or co-pilot life raft 

deployment handle (handle), part number 

(P/N) ASI–700–45, certificated in any 

category. 

Compliance: Required within 100 hours 

time-in-service, unless accomplished 

previously. 

To prevent the bending of the handle, 

which could result in failure of the life raft 

to deploy, resulting in the loss of access to 

the life raft after an emergency ditching on 

water, accomplish the following: 

(a) Install the safety pins, P/N ASI–625–14, 

to lock out the raft deployment pods. 

(b) Remove the pad, P/N BA7601. 

(c) Remove the top cover, P/N ASI–700–73. 

(d) Remove the cotter pin, P/N AN381–2– 

8, from the clevis pin, P/N MS 20392–2C9, 

located at the crew release handle assembly. 

(e) Remove the washer, P/N AN960–10L, 

and clevis pin from the cable, P/N 2604750– 

90. 

(f) Disconnect the cable from the handle, 

and secure the cable to the broom closet to 

prevent it from falling into the lower cover. 

(g) Remove the handle by removing the 

bolt, P/N AN4–11, nut, P/N MS20364–428A, 

and washers, P/N AN960–416L, from the raft 

deployment handle assembly (handle 

assembly), P/N ASI–700–41A. 

(h) Remove the safety pin, P/N ASI–700– 

80. 

(i) Remove and discard any ball bearings, 

and clean all surfaces of the remaining 

handle assembly. 

(j) Install the handle, P/N ASI–700–49A. 

(k) Reinstall the bolt, nut, and washers, 

P/N AN960–416L, and install the washer, 

P/N ASI–700–44, between the handle and the 

mount, 

P/N ASI–700–43, on the left side of the 

broom closet, and torque to 20 in-lb 

maximum. 

(l) Reinstall the safety pin. 

(m) Release the cable from the broom 

closet. 

(n) Reinstall the cable to the handle with 

the clevis pin. 

(o) Reinstall the washer, P/N AN960–10L, 

and the cotter pin on to the clevis pin. 

(p) Reinstall the top cover. 

(q) Reinstall the pad. 

(r) Remove the raft deployment pod lock 

out safety pins. 

Note: Aero Seats and Systems, Inc., Alert 

Service Bulletin No. 76–500–02, Revision C, 

dated September 16, 2010, which is not 

incorporated by reference, contains 

additional information about the subject of 

this airworthiness directive. 

(s) 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 Manager, Rotorcraft 

Certification Office, FAA, Attn: Martin Crane, 

Aerospace Engineer, FAA, Rotorcraft 

Directorate, Rotorcraft Certification Office, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax (817) 

222–5783, e-mail Martin.R.Crane@faa.gov for 

information about previously approved 

alternative methods of compliance. 

(t) The Joint Aircraft System/Component 

(JASC) Code 2564: is: Life raft. 

Issued in Fort Worth, Texas, on January 27, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–4477 Filed 2–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 121 

[Docket No. FAA–2011–0045] 

Proposed Legal Interpretation 

AGENCY: Federal Aviation 

Administration (FAA). 

ACTION: Proposed interpretation. 

SUMMARY: The FAA is considering 

clarifying the application of flight time 

limitations and rest requirements in 14 

CFR 121.481 and 121.483 for pilots 

operating in flag operations as part of a 

two-pilot crew and as part of a two-pilot 

crew and one additional flightcrew 

member during a seven-day period. 

DATES: Comments must be received on 

or before May 2, 2011. 

ADDRESSES: You may send comments 

identified by Docket Number FAA– 

2011–0045 using any of the following 

methods: 

Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

Hand Delivery or Courier: Bring 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Fax: Fax comments to Docket 

Operations at 202–493–2251. 

FOR FURTHER INFORMATION CONTACT: Sara 

Mikolop, Attorney, Regulations 

Division, Office of the Chief Counsel, 

Federal Aviation Administration, 800 

Independence Avenue, SW., 

Washington, DC 20591; telephone: 202– 

267–3073. 

SUPPLEMENTARY INFORMATION: The FAA 

provides flight time and rest 

requirements for flightcrew members 

used in flag operations in 14 CFR 

subpart R. Within subpart R, § 121.481 

provides flight time limitations for oneor two-pilot crews and § 121.483 

provides flight time limitations for 

crews of two pilots and one additional 

flight crewmember. 

The flight time limitations are more 

restrictive for operations under 

§ 121.481 than § 121.483 because the 

crew size is smaller and thus each pilot 

must assume responsibilities for more 

in-flight duties. See Legal Interpretation 

from Donald P. Byrne to James W. 

Johnson (August 24, 1999). In contrast, 

when a crew of two pilots and one 

additional flightcrew member operates 

under § 121.483, the in-flight duties are 

divided among more crewmembers and 

so the overall burden on any one 

crewmember may be reduced as 

crewmembers rotate through flight deck 

duties and may be provided an 

opportunity for rest. See Legal 

Interpretation from Donald P. Byrne to 

James W. Johnson (August 24, 1999). 

Thus, when the number of flightcrew 

members used in a flag operation 

increases, Subpart R allows for 

increased flight time. Compare 14 CFR 

121.481 with 14 CFR 121.483 and 14 

CFR 121.485. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS