Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66615 

Applicability: Model EC225LP helicopters, 

with an airworthiness certificate issued 

before December 15, 2009, with FISHER 

H140 pilot and co-pilot seats, part number 

(P/N) 052010032000D61091, Eurocopter P/N 

704A41120116, or with Eurocopter co-pilot 

seat, P/N 332V08–0180–00, installed, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect a missing floor attachment screw, 

nut, or washer to help prevent detachment of 

the seat from the floor during an emergency 

landing, do the following: 

(a) Within 85 hours time-in-service (TIS), 

inspect for the presence of 4 screws and 4 

nuts on each side of the copilot’s seat mount 

and 1 screw and 1 nut on each side of the 

pilot’s seat mount by reference to Figures 1 

through 4 of Eurocopter Alert Service 

Bulletin No. 53A020, Revision 0, dated 

February 17, 2010 (ASB). 

(b) If any screw, nut, or cup washer is 

missing, remove the seat and mount and 

before further flight, countersink the hole and 

install airworthy parts and replace the mount 

and seat by following the Accomplishment 

Instructions, paragraph 2.b.2.b., of the ASB. 

(c) 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, Safety 

Management Group, FAA, Attn: Gary Roach, 

Aviation Safety Engineer, Rotorcraft 

Directorate, Regulations and Guidance 

Group, 2601 Meacham Blvd., Fort Worth, 

Texas 76137, telephone (817) 222–5130, fax 

(817) 222–5961, for information about 

previously approved alternative methods of 

compliance. 

(d) The Joint Aircraft System/Component 

Code is 2500: Cabin Equipment/Furnishings. 

(e) The inspection and repair of the pilot 

and co-pilot seats shall be done by following 

the specified portions of Eurocopter Alert 

Service Bulletin No. 53A020, Revision 0, 

dated February 17, 2010. 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 American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas, 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. 

(f) This amendment becomes effective on 

November 14, 2011. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2010–0030, dated February 26, 2010. 

Issued in Fort Worth, Texas, on September 

29, 2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27680 Filed 10–26–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0792; Directorate 

Identifier 2009–SW–19–AD; Amendment 39– 

16762; AD 2011–16–04] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

S–92A Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Sikorsky Model S–92A helicopters. This 

action requires making pen and ink 

changes, inserting a copy of this AD, or 

inserting specified temporary revisions 

into the Limitations section of the 

Rotorcraft Flight Manual (RFM) limiting 

the maximum rolling groundspeed for a 

normal landing or takeoff from 65 knots 

to 50 knots for helicopters with a certain 

serial-numbered landing gear retract 

actuator (actuator). Instead of limiting 

the groundspeed, replacing the affected 

actuator with a modified actuator is 

terminating action for the requirements 

of this AD. This amendment is 

prompted by a report of a main landing 

gear that would not retract. The 

manufacturer reports that certain 

actuators were manufactured with 

down-lock keys that did not meet the 

specified minimum hardness 

requirements. This condition, if not 

corrected, could lead to a landing gear 

collapse following a roll-on landing that 

exceeds 50 knots groundspeed. These 

actions are intended to prevent collapse 

of a landing gear and subsequent loss of 

control of the helicopter. 

DATES: Effective November 14, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 27, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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 AD from Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (203) 383–4866, 

e-mail address tsslibrary@sikorsky.com, 

or at http://www.sikorsky.com. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or 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. 

FOR FURTHER INFORMATION CONTACT: 

Michael Schwetz, Aviation Safety 

Engineer, Boston Aircraft Certification 

Office, 12 New England Executive Park, 

Burlington, MA 01803, telephone (781) 

238–7761, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for 

Sikorsky Model S–92A helicopters. This 

action requires making pen and ink 

changes, inserting a copy of this AD, or 

inserting certain temporary revisions 

into the Limitations section of the RFM 

limiting the maximum groundspeed for 

a normal landing or takeoff to 50 knots 

for helicopters with a certain serialnumbered actuator installed. The 

temporary revisions to the Limitations 

section of the RFM also require 

replacing the actuators if the landing 

exceeds the 50 knot rolling groundspeed 

before further flight or before towing the 

helicopter; rolling ground taxi 

operations are permitted. Replacing the 

affected actuator with a modified 

actuator is terminating action for the 

requirements of this AD. The 

manufacturer states that it anticipates 

retrofitting the fleet with a modified 

actuator within 3 years. This 

amendment is prompted by a report that 

certain actuators were manufactured 

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66616 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 

with a down-lock pin that does not meet 

the specified minimum hardness 

requirements, which could lead to a 

landing gear collapse following a roll-on 

landing that exceeds 50 knots. These 

actions are intended to prevent a 

landing gear collapse and subsequent 

loss of control of the helicopter. 

We have reviewed Sikorsky Alert 

Service Bulletin No. 92–32–001, dated 

May 2, 2008 (ASB), which describes the 

unsafe condition, its cause, and the 

temporary operating restrictions 

intended to mitigate the unsafe 

condition until modified actuators are 

available. The ASB references and 

includes Embraer Liebherr 

Eqiupamentos do Brasil Service Bulletin 

No. 2392–0850–32–02 Change No. 1, 

dated May 15, 2008, which specifies 

procedures for replacing the down-lock 

key in the affected actuators. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD is 

being issued to limit the maximum 

rolling groundspeed for a normal 

landing or takeoff to 50 knots rolling 

groundspeed. If the limitation is 

exceeded on landing, the actuator must 

be replaced with a modified actuator 

before further flight or towing operation; 

rolling ground taxi operations are 

permitted. This AD requires making pen 

and ink changes, inserting a copy of this 

AD, or inserting the following 

temporary revisions into the Limitations 

section of the RFM: SA S92A–RFM–000, 

Revision 2; SA S92A–RFM–002, 

Revision 6; SA S92A–RFM–003, 

Revision 5; SA S92A–RFM–004, 

Revision 5; SA S92A–RFM–005, 

Revision 4; or SA S92A–RFM–006, 

Revision 3; all approved on January 7, 

2011. Instead of limiting the 

groundspeed, replacing each actuator 

without the modification letter ‘‘B’’ 

stamped on the nameplate with an 

airworthy modified actuator with a 

letter ‘‘B’’ stamped on the nameplate 

constitutes terminating action for the 

requirements of this AD. 

The short compliance time of before 

further flight is required because the 

previously described critical unsafe 

condition can adversely affect the 

structural integrity and controllability of 

the helicopter. Therefore, limiting the 

maximum groundspeed for normal 

landing or takeoff to 50 knots to reduce 

the likelihood of a landing gear collapse 

is required before further flight and this 

AD must be issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will affect 

42 helicopters. It will take a minimal 

amount of time to make the limitation 

changes. If the operator replaces an 

affected actuator with a modified 

actuator, it will take about 8 work hours 

at an average labor rate of $85 per work 

hour. Required parts will cost about 

$7,841 per helicopter. Based on these 

figures, we estimate the total cost 

impact of the AD on U.S. operators to 

be $357,882, assuming all the helicopter 

operators install modified actuators. 

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 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2011–0792; 

Directorate Identifier 2009–SW–19–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:// 

www.regulations.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, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent 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). 

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 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD. See the AD docket to examine 

the 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 

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, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends part 39 of the 

Federal Aviation Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2011–16–04 Sikorsky Aircraft Corporation: 

Amendment 39–16762. Docket No. 

FAA–2011–0792; Directorate Identifier 

2009–SW–19–AD. 

Applicability: Model S–92A helicopters 

with landing gear retract actuator (actuator), 

part number (P/N) 92250–00800–103, with a 

serial number (S/N) 101–00026 through 101– 

00237, without the modification letter ‘‘B’’ 

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Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66617 

stamped on the nameplate, certificated in any 

category. 

Compliance: Before further flight, unless 

previously accomplished. 

To prevent a landing gear collapse and 

subsequent loss of control of the helicopter, 

do the following: 

(a) Revise the operating limitations, 

‘‘Airspeed Limits’’ section of the rotorcraft 

Flight Manual (RFM) by one of the following 

methods: 

(1) Insert Sikorsky ‘‘Temporary Revisions’’ 

SA S92A–RFM–000, Revision 2; SA S92A– 

RFM–002, Revision 6; SA S92A–RFM–003, 

Revision 5; SA S92A–RFM–004, Revision 5; 

SA S92A–RFM–005, Revision 4; or SA 

S92A–RFM–006, Revision 3; all approved 

January 7, 2011; or 

(2) Insert a copy of this AD; or 

(3) Make pen and ink changes with the 

following limitations: 

‘‘Maximum rolling groundspeed for normal 

takeoff or normal landing is 50 knots.’’ 

‘‘After a landing with a rolling 

groundspeed in excess of 50 knots, any 

further takeoffs or towing operation is 

prohibited. Rolling ground taxi operations of 

less than 50 knots are permitted.’’ 

(b) Following a landing with a rolling 

groundspeed in excess of 50 knots, or as an 

alternative to revising the operating 

limitations section of the RFM in compliance 

with this AD, before further flight, replace 

each affected actuator that does not have the 

modification letter ‘‘B’’ stamped on the 

nameplate with an airworthy actuator that 

has the modification letter ‘‘B’’ stamped on 

the nameplate. 

(c) 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, Boston Aircraft 

Certification Office, FAA, ATTN: Michael 

Schwetz, Aviation Safety Engineer, 12 New 

England Executive Park, Burlington, MA 

01803, telephone (781) 238–7761, fax (781) 

238–7170, for information about previously 

approved alternative methods of compliance. 

Note: Sikorsky Alert Service Bulletin No. 

92–32–001, dated May 2, 2008, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. 

(d) The Joint Aircraft System/Component 

(JASC) Code is 3233: Landing Gear Actuator. 

(e) This amendment becomes effective on 

November 14, 2011. 

Issued in Fort Worth, Texas, on July 14, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27773 Filed 10–26–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0909; Directorate 

Identifier 2010–SW–026–AD; Amendment 

39–16835; AD 2011–21–12] 

RIN 2120–AA64 

Airworthiness Directives; Erickson AirCrane Incorporated Model S–64F 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

Erickson Air-Crane (Erickson Air-Crane) 

Model S–64F helicopters. The 

amendment requires, at specified 

intervals, certain inspections of the 

rotating swashplate assembly 

(swashplate) for a crack. If a crack is 

found, this AD also requires, before 

further flight, replacing the swashplate 

with an airworthy swashplate. This AD 

is prompted by a report from the 

manufacturer of a swashplate cracking 

during fatigue testing. We are issuing 

this AD to prevent loss of a swashplate 

due to a fatigue crack, loss of control of 

the main rotor system, and subsequent 

loss of control of the helicopter. 

DATES: Effective December 1, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 1, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Erickson 

Air-Crane Incorporated, 3100 Willow 

Springs Road, P.O. Box 3247, Central 

Point, OR 97502, telephone (541) 664– 

5544, fax (541) 664–2312. 

Examining the AD Docket: You may 

examine the AD docket, 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 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, ASW–170, Aviation 

Safety Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, Fort 

Worth, Texas 76137, telephone (817) 

222–5170, fax (817) 222–5783. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a Notice of Proposed 

Rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to Erickson Air-Crane Model S– 

64F helicopters on September 3, 2010. 

That NPRM was published in the 

Federal Register on September 16, 2010 

(75 FR 56487). That NPRM proposed to 

require, at specified intervals, certain 

visual inspections of the swashplate for 

a crack. Also, the AD proposed, at 

specified intervals a fluorescentpenetrant inspection (FPI) of the 

swashplate for a crack. If a crack is 

found, that NPRM proposed, before 

further flight, replacing the swashplate 

with an airworthy swashplate. 

Comments 

We gave the public an opportunity to 

participate in developing this AD. We 

received no comment on the NPRM or 

on our determination of the cost to the 

public. Therefore, based on our review 

and evaluation of the available data, we 

have determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 7 

helicopters of U.S. registry and will take 

about: 

• .5 hour for the visual inspection; 

• 1 hour for the 10-power or higher 

magnifying glass inspection; 

• 35 hours for the 1,000-hour FPI; and 

• 32 hours to replace a swashplate at 

an average labor rate of $85 per work 

hour. 

Required parts will cost about $25,000 

per helicopter. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators is $229,145, assuming 40 15- 

hour visual inspections; 4 150-hour 10- 

power magnifying glass inspections; 1 

1000-hour FPI and 1 swashplate 

replacement for each helicopter for the 

entire fleet of S–64F helicopters for each 

year. 

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 

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