Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules 44045 

would require 0.5 work-hour, for a cost 

of $43 per helicopter. The labor cost of 

installing paper in the flight manual 

would be negligible for a helicopter. 

• Replacing the MRH assembly would 

require 24 work-hours and parts would 

cost $5,000, for a total cost of $7,040 per 

helicopter. 

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 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. 

For the reasons discussed, I certify 

this 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by Reference, 

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 airworthiness 

directive (AD): 

EUROCOPTER FRANCE HELICOPTERS 

(Eurocopter): Docket No. FAA–2013– 

0635; Directorate Identifier 2012–SW– 

081–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

EC225LP helicopters with a main rotor hub 

(MRH) assembly with a rotating swashplate, 

part number (P/N) 332A31–3074–00 or 

332A31–3076–00, and stationary swashplate, 

P/N 332A31–3079–00 or 332A31–3079–01, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

corrosion or a crack in the stationary or 

rotating swashplate of the MRH assembly, 

which could lead to failure of the swashplate 

and subsequent loss of helicopter control. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(d) Required Actions 

(1) Within 110 hours time-in-service (TIS) 

or before the MRH assembly accumulates 

1,320 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 1,320 

hours TIS, visually inspect the rotating and 

stationary swashplates for corrosion or a 

crack by following the Accomplishment 

Instructions, paragraph 3.B.2 and Figures 1 

through 3, of Eurocopter Alert Service 

Bulletin No. EC225–05A030, Revision 0, 

dated July 12, 2012 (ASB). 

(2) If a crack exists in the rotating or 

stationary swashplates, replace the MRH 

assembly with an airworthy MRH. 

(3) If corrosion exists without any visual 

indication of cracking, do the following: 

(i) Before further flight, install a placard 

stating ‘‘NO FLIGHT IN OAT BELOW ¥30 

°C’’ in the full view of the pilots and add the 

statement ‘‘NO FLIGHT IN OAT BELOW 

¥30 °C’’ to the Operating Limitations Section 

of the helicopter’s Rotorcraft Flight Manual 

(RFM) by making pen and ink changes or by 

inserting a copy of this AD in Section 2.3 

Flight Envelope, Item 2 Temperature Limits. 

(ii) Within 150 hours TIS or 6 months after 

the inspection when the corrosion was first 

detected, whichever occurs first, replace the 

MRH assembly with an airworthy assembly. 

Remove any placard that states ‘‘NO FLIGHT 

IN OAT BELOW ¥30 °C’’ from the helicopter 

and remove any related limitation from the 

RFM. 

(4) Replacement of an MRH assembly does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(d)(1) of this AD. 

(e) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

(2) For operations conducted under a 14 

CFR Part 119 operating certificate or under 

14 CFR Part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(f) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) AD 

No. 2012–0131, dated July 31, 2012. You may 

view a copy of the EASA AD in the AD 

Docket on the Internet at http:// 

www.regulations.gov. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6230, Main Rotor Mast/Swashplate. 

Issued in Fort Worth, Texas, on July 11, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–17628 Filed 7–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0636; Directorate 

Identifier 2012–SW–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Sikorsky Model S–70, S–70A, and S– 

70C helicopters. This proposed AD 

would establish a new life limit based 


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on a prorated formula for certain 

identified components (parts) installed 

on Model S–70, S–70A, and S–70C 

helicopters after being previously 

installed on certain military model 

helicopters. This proposed AD is 

prompted by the discovery that certain 

parts have been interchanged between 

military helicopter models with 

different life limits and the possibility 

that these same parts can be 

interchanged with civilian models with 

different life limits. The proposed 

actions are intended to establish a prorated in service life limit for each 

identified part to prevent fatigue failure 

of a part and subsequent loss of control 

of the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 23, 

2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket 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 AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Michael Davison, Flight Test Engineer, 

Boston Aircraft Certification Office, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

Massachusetts 01803; telephone (781) 

238–7156; email 

michael.davison@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

We propose to adopt a new AD for 

Sikorsky Model S–70, S–70A and S–70C 

helicopters. Certain parts on Model S– 

70, S–70A, and S–70C helicopters are 

common to military Model UH–60M 

and SH–60B/F helicopters. These parts 

have identical part numbers. However, 

the part life limits may be different on 

the military models and are often lower 

due to higher usage and flight load 

spectrum. This proposed AD is 

prompted by the discovery that 

personnel at a military depot had 

installed military Model UH–60M parts 

on military Model UH–60A/L 

helicopters. Because the civilian Model 

S–70 series helicopters are derived from 

the military Model UH–60, it is possible 

that parts previously installed on 

military aircraft with a lower life limit 

could inadvertently be later installed on 

civil aircraft. This proposed AD would 

require establishing a pro-rated life limit 

for each affected part to account for the 

heavier usage when previously installed 

on the Model UH–60M or SH–60B/F. 

The proposed actions are intended to 

establish appropriate remaining inservice lives to identified parts to 

prevent fatigue failure of a part and 

subsequent loss of control of the 

helicopter. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

this same type design. 

Proposed AD Requirements 

This proposed AD would require, 

within 25 hours time-in-service, 

inserting the component life prorating 

formula into the airworthiness 

limitation section of the maintenance 

manual or instructions for continued 

airworthiness, calculating the new life 

limit for each part by applying the 

formula, and establishing life limits for 

certain parts without applying the 

formula. Furthermore, the proposed AD 

would require updating the component 

log or equivalent record with the new 

in-service life limit. This proposed AD 

would also require replacing each part 

that has reached or exceeded its new life 

limit with an airworthy part. Lastly, this 

proposed AD would prohibit installing 

any applicable part on a Model S–70, S– 

70A, or S–70C helicopter if the number 

of hours is unknown and would 

prohibit installing certain parts on a 

Model S–70, S–70A, or S–70C 

helicopter if they have been previously 

installed on a Model UH–60M 

helicopter. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 9 helicopters of U.S. 

Registry. 

We estimate that the cost to insert the 

pages into the TM would be negligible. 

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 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 


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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, I certify 

this 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

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 airworthiness 

directive (AD): 

Sikorsky Aircraft Corporation (Sikorsky): 

Docket No. FAA–2013–0636; Directorate 

Identifier 2012–SW–065–AD. 

(a) Applicability 

This AD applies to Model S–70, S–70A, 

and S–70C helicopters, certificated in any 

category, with the following parts installed: 

(1) Spindle and liner assembly, part 

number (P/N) 38023–10374–041; 

(2) Main Rotor Hub, P/N 70070–10046–055 

and –056; 

(3) Main Rotor Spindle nut, P/N 70102– 

08105–102; 

(4) Main Rotor Control Horn, P/N 70102– 

08111–047; 

(5) Main Rotor Hub, P/N 70103–08112–041 

and –047; 

(6) Rotating Swashplate, P/N 70104– 

08001–044 and –045; 

(7) Main rotor Shaft Extension, P/N 70351– 

08186–043; 

(8) Main Rotor Gear Box Housing, P/N 

70351–38110–043, –044, and –045; 

(9) Main Rotor Shaft, P/N 70351–38131– 

042; 

(10) Output Bevel Gear and Shaft, P/N 

70358–06620–101 and –102; 

(11) Left Tie Rod Assembly, P/N 70400– 

08115–043, –045, –046, and –047; 

(12) Forward Bellcrank Support Assembly, 

P/N 70400–08162–042; 

(13) Lateral Servo Bellcrank, P/N 70400– 

08166–041; or 

(14) Tail rotor Servo Assembly, P/N 70410– 

06520–044 through –046. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

critical part remaining in service beyond its 

life limit due to previously being installed on 

a different helicopter model with higher 

usage and flight loads. This condition could 

result in fatigue failure of a critical part and 

subsequent loss of control of the helicopter. 

(c) Comments Due Date 

We must receive comments by September 

23, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 25 hours time-in-service (TIS): 

(i) Insert into the airworthiness limitation 

section of the maintenance manual or 

instructions for continued airworthiness the 

component life prorating formula in Section 

1.1.3 of Sikorsky Technical Manual TM 1– 

70–23AW–2, Change 3, dated April 15, 2012. 

(ii) Using the service life limits in Table 1 

to paragraph (e) of this AD, apply the 

component life prorating formula and 

calculate the new life limit for each specified 

part. If the number of hours of a part is 

unknown, that part cannot be installed on a 

Sikorsky Model S–70, S–70A, or S–70C 

helicopter. Do not calculate a new life limit 

for the part where the Model SH–60 life limit 

is higher than the life limit on Models S–70, 

S–70A, and S–70C. 

TABLE 1 TO PARAGRAPH (e) 

P/N Part description 

S–70, S–70A, 

S–70C Service 

life 

UH–60M 

Service life 

SH–60B/F 

Service life 

38023–10374–041 ................................................. Spindle and Liner Assembly .................... 8,000 6,400 10,000 

70070–10046–055 and –056 ................................ Main Rotor Hub ....................................... 5,100 3,100 N/A1

70102–08105–102 ................................................. Main Rotor Spindle Nut ........................... 8,000 6,400 10,000 

70102–08111–047 ................................................. Main Rotor Control Horn ......................... 20,000/1,300 2/ 

2,500 2

10,000 N/A1

70103–08112–041 and –047 ................................ Main Rotor Hub ....................................... 5,100 3,100 N/A1

70104-08001-044-045 ........................................... Rotating Swashplate ................................ 11,000 4,600 9,600 

70351–08186–043 ................................................. Main Rotor Shaft Extension ..................... 14,000 4,900 16,000 

70351–38110–043, –044, and –045 ..................... Main Rotor Gear Box Housing ................ 11,000 4,000 9,000 

70351–38131–042 ................................................. Main Rotor Shaft ...................................... 17,000 5,200 19,000 

70358–06620–101 and –102 ................................ Output Bevel Gear and Shaft .................. 5,000 1,800 N/A1

70400–08115–043, –045, –046, and -047 ............ Left Tie Rod Assembly ............................ 14,000 4,600 6,300 

70400–08162–042 ................................................. Forward Bellcrank Support Assembly ..... 14,000/2,500 3 5,600 7,600 

70400–08166–041 ................................................. Lateral Servo Bellcrank ........................... 20,000 11,000 14,000 

70410–06520–044 through –046 .......................... Tail Rotor Servo Assembly ...................... 15,000 11,000 N/A1

1There is no service life limit listed because the parts on Model SH–60B/F have a different P/N than the parts on Models S–70, S–70A, and 

S–70C. 2For serial number (S/N) 32479930 through 324791859, with CAGE code 60078, the life limit is 1,300 hours TIS. 

For S/N A241–07543 through A241–07594, A241-07706 through A241–07755, A241-07768 through A241–07771, A241–07800 through A241– 

07831, R241–00101 through R241–00355, R241–00701 through R241-00966, and R241–01001 through R241-01166, the life limit is 2,500 hours 

TIS. 3For S/N A–367–00001 through A367–00035, with CAGE code 78286, the life limit is 2,500 hours TIS. 


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(iii) Record the newly-established life limit 

of each part on the part’s component log card 

or equivalent record. 

(2) After establishing the new life limit, 

replace each part that has reached or 

exceeded its new life limit with an airworthy 

part before further flight. 

(3) Do not install the following parts on a 

Model S–70, S–70A, or S–70C helicopter if 

they have been previously installed on a 

Model UH–60M helicopter: 

(i) Bolt, self retaining, P/N 70103–08801– 

102; 

(ii) Bifilar, P/N 70107–08400–046; (iii) Aft 

Bellcrank, P/N 70400–08102–045; 

(iv) Aft Walking Beam Assembly, P/N 

70400–08104–048; or 

(v) Close Tolerance Bolt, P/N 70400– 

26802–102 and –103. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Michael Davison, Flight Test Engineer, 

Boston Aircraft Certification Office, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, Massachusetts 

01803; telephone (781) 238–7156; email 

michael.davison@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220 Main Rotor Hub, 6230 Main Rotor 

Mast/Swashplate, 6320 Main Rotor Gearbox, 

6310 Engine/Transmission Coupling, 6510 

Tail Rotor Drive Shaft. 

Issued in Fort Worth, Texas, on July 11, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–17629 Filed 7–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0637; Directorate 

Identifier 2013–SW–030–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

Sikorsky Model S–76A, B, and C 

helicopters. The existing AD currently 

requires inspecting the main rotor lower 

bifilar arm assembly (bifilar arm 

assembly) for a crack, and if there is a 

crack, replacing the bifilar arm 

assembly. The AD also requires a onetime test for the correct torque on the 

lug nuts, and if necessary, conducting 

torque stabilization tests. Since we 

issued that AD, Sikorsky has developed 

a terminating procedure for the 

inspections required by the existing AD. 

This proposed AD would retain the 

requirements of that AD, and would 

require replacing the main rotor hub 

(MRH) pilot with a different partnumbered MRH pilot, which would be 

terminating action for the requirements 

of the AD. The proposed actions are 

intended to prevent failure of a bifilar 

lug, damage to the main rotor control 

system, and subsequent loss of control 

of the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 23, 

2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket 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 AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed AD, contact Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT 06614; telephone (800) 

562–4409; email 

tsslibrary@sikorsky.com; or at http:// 

www.sikorsky.com. You may review 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Nicholas Faust, Aviation Safety 

Engineer, Boston Aircraft Certification 

Office, Engine & Propeller Directorate, 

12 New England Executive Park, 

Burlington, Massachusetts 01803; 

telephone (781) 238–7763; email 

nicholas.faust@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On October 26, 2005, we issued AD 

2005–22–01, amendment 39–14345 (70 

FR 61721) for Sikorsky Model S–76A, B, 

and C helicopters with an MRH pilot 

part number (P/N) 76103–08003–101 

with 1,500 or more hours time-inservice (TIS) installed. The AD requires, 

every 50 hours TIS, inspecting the main 

rotor lower bifilar arm assembly in the 

attachment area around the lower bifilar 

lugs for a crack. If there is a crack, the 

AD requires replacing the bifilar arm 

assembly. If there is not a crack, the AD 

requires a one-time test for the correct 

torque on the lug nuts, and if necessary, 

conducting torque stabilization tests. 

The AD was prompted by four reports 


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