This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

55453 

Vol. 75, No. 176 

Monday, September 13, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0609; Directorate 

Identifier 2008–SW–24–AD; Amendment 

39–16408 AD 2010–17–16] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S–76A, 

S–76B, and S–76C Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S–76A, S–76B, and S–76C 

helicopters. This AD requires an initial 

and recurring inspections of the tail 

rotor vertical stabilizer aft spar assembly 

(aft spar assembly) for a crack, loose or 

working fasteners, and corrosion, and, if 

any are found, further inspections of the 

vertical stabilizer forward spar assembly 

(forward spar assembly). Repairing or 

replacing any unairworthy part before 

further flight is also required. This AD 

also requires a recurring track-andbalance of the tail rotor. Finally, this AD 

requires installing a vertical stabilizer 

modification kit, which is terminating 

action for the requirements of the AD. 

This AD is prompted by 26 reports of 

fatigue cracks in the aft spar assembly 

web and outer caps. The actions 

specified by this AD are intended to 

detect and correct an unbalanced or outof-track tail rotor, which could lead to 

increased vibrations, a fatigue crack, 

loss of a portion of the vertical stabilizer 

and subsequent loss of control of the 

helicopter. 

DATES: Effective October 18, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of October 18, 

2010. 

ADDRESSES: 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, Connecticut 06614, 

phone (203) 383–4866, e-mail address 

tsslibrary@sikorsky.com. 

Examining the Docket: You may 

examine the docket that contains this 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov or at the Docket 

Operations office, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

Nicholas Faust, Aviation Safety 

Engineer, 16 New England Executive 

Park, Burlington, MA 01803; telephone: 

(781) 238–7763; fax: (781) 238–7170. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for certain Sikorsky 

Model S–76A, S–76B, and S–76C 

helicopters was published in the 

Federal Register on June 4, 2008 (73 FR 

31780). The proposed action applied to 

Sikorsky Model S–76A, S–76B, and 

S–76C helicopters with any of the 

following part-numbered aft spar 

assemblies installed: 

Helicopter model 

Aft spar assembly 

part number 

(P/N) 

S–76A ......................... 76201–05002–114 

76201–05002–115 

S–76B and S–76C ...... 76201–05002–047 

76201–05002–048 

76201–25002–041 

76201–25002–044 

76201–25002–045 

76201–25002–046 

That action proposed to require, for any 

spar assembly that has 1,000 or more 

hours time-in-service (TIS), within 30 

days and thereafter at intervals not to 

exceed 50 hours TIS, inspecting the aft 

spar assembly, and if you find a crack, 

a loose or working fasteners, or 

corrosion, inspecting the forward spar 

assembly before further flight and 

replacing or repairing any unairworthy 

part with an airworthy part before 

further flight. The action also proposed 

to require, within 30 days and thereafter 

at intervals not to exceed 200 hours TIS, 

track-and-balance of the tail rotor. 

Accomplishing the tail rotor track-andbalance would involve both a pilot and 

mechanic. The pilot’s function would be 

to operate the helicopter to a ‘‘light on 

wheels’’ state—almost to the point of 

takeoff, and the mechanic would 

accomplish the vibration measurements. 

Also, proposed was requiring, on or 

before December 31, 2010, installing a 

vertical stabilizer modification kit, P/N 

76070–20562, 76070–20563, or 76070– 

20564, which would be terminating 

action for the requirements of the 

proposed AD. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the one 

comment received from the 

manufacturer. 

Sikorsky states that the effectivity 

should also include the aircraft serial 

number as referenced in their Alert 

Service Bulletin (ASB) No. 76–55–21. 

Sikorsky recommends the following 

wording ‘‘Note All S–76 helicopter serial 

numbers greater than 760578 but not 

including helicopter serial number 

762976 are not affected.’’ Sikorsky states 

that ‘‘this would ease the operator 

burden for aircraft built after the 

affected population of verifying the spar 

part numbers to show compliance with 

the AD.’’ We concur with Sikorsky’s 

recommendation to limit the 

applicability to only specified serial 

numbered helicopters and have revised 

the AD accordingly. Further, we 

inadvertently omitted the dash numbers 

to the part numbers of the modification 

kits contained in paragraph (c) of the 

proposed AD; ‘‘–011’’ has been added to 

each of the part numbers in this final 

rule. 

We have reviewed the following 

service information: 

• Sikorsky Alert Service Bulletin 

(ASB) No. 76–55–20A, Revision A, 

dated November 11, 2003 (76–55–20A), 

that applies to Sikorsky Model S–76A 

and Model S–76C helicopters and 

describes procedures for a one-time 

inspection of the vertical stabilizer aft 

spar assembly for cracks, loose or 

working fasteners, and/or corrosion, and 

if necessary an inspection of the forward 

spar assembly. 

• ASB No. 76–65–58A, Revision A, 

dated November 11, 2003 (76–65–58A), 

that applies to all Sikorsky Model S–76 


srobinson on DSKHWCL6B1PROD with RULES
55454 Federal Register / Vol. 75, No. 176 / Monday, September 13, 2010 / Rules and Regulations 

serial numbered helicopters up to and 

including 760526 and describes 

procedures for an initial enhanced tail 

rotor balance check. 

We have also reviewed ASB No. 

76–55–21, dated February 9, 2006 (76– 

55–21), that Sikorsky references it its 

comment. ASB 76–55–21 applies to all 

Sikorsky S–76 serial numbered 

helicopters up to an including 760578 

and 762976 and specifies the 

installation of a structural enhancement 

kit which strengthens the aft spar 

assembly, improves the fatigue strength 

capability of the vertical stabilizer, and 

extends the vertical stabilizer 

inspection. We do not reference ASB 

No. 76–55–21 in the compliance 

instructions of this AD. 

This AD differs from ASB 76–55–20A 

and ASB 76–65–58A in that the 

incorporated by reference provisions 

described in ASB No. 76–55–20A are 

required for the Model S–76B 

helicopters as well as for the Model 

S–76A and Model S–76C helicopters. 

Also, this AD requires repetitive 

inspections of the aft spar assembly and 

the forward spar assembly, if necessary, 

and repetitive track-and-balance of the 

tail rotor, whereas the two ASBs specify 

only a one-time tail rotor balance check 

and an aft spar assembly inspection and, 

if necessary, a one-time forward spar 

assembly inspection. 

After careful review of the available 

data, including the comment noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. We have also 

increased the labor rate for performing 

the required actions from $80 to $85 per 

work-hour. We have determined that 

these changes will not significantly 

increase the economic burden on any 

operator nor increase the scope of 

the AD. 

We estimate that this AD will affect 

216 helicopters of U.S. registry. We also 

estimate that the inspections for a crack, 

a loose or working fastener, or corrosion 

will take approximately 7 work-hours 

per helicopter to accomplish. The tail 

rotor track-and-balance procedures and 

adjustments will take approximately 10 

work-hours per helicopter, and 

installing the vertical stabilizer 

modification kit will take approximately 

120 hours per helicopter, at an average 

labor rate of $85 per work hour. The 

vertical stabilizer modification kit will 

cost approximately $4,250. Based on 

these figures, we estimate the total cost 

impact of this AD on U.S. operators to 

be $5,214,240, assuming that, on each 

helicopter, 12 spar assembly inspections 

are done ($1,542,240), that 3 tail rotor 

track-and-balance procedures are done 

($550,800), that no spar assembly is 

repaired or replaced, and that the 

vertical stabilizer modification kit is 

installed. 

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, under 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. FAA amends § 39.13 by adding a 

new AD to read as follows: 

2010–17–16 Sikorsky Aircraft Corporation: 

Amendment 39–16408; Docket No. 

FAA–2008–0609; Directorate Identifier 

2008–SW–24–AD. 

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

S–76C helicopters, with serial numbers 

76005 through 760578, inclusive, and serial 

number 762976, with any of the following 

part-numbered vertical stabilizer aft spar 

assemblies having 1,000 or more hours timein-service (TIS) installed, certificated in any 

category. 

Helicopter model 

Vertical stabilizer aft 

spar assembly part 

number 

S–76A ......................... 76201–05002–114 

76201–05002–115 

S–76B and S–76C ...... 76201–05002–047 

76201–05002–048 

76201–25002–041 

76201–25002–044 

76201–25002–045 

76201–25002–046 

Compliance: Required as indicated. 

To detect and correct an unbalanced or 

out-of-track tail rotor, which could lead to 

increased vibrations, a fatigue crack, loss of 

a portion of the vertical stabilizer, and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Within 30 days, unless accomplished 

previously, and thereafter at intervals not to 

exceed 50 hours TIS, inspect the vertical 

stabilizer aft spar assembly (aft spar 

assembly) for a crack, a loose or working 

fastener, or corrosion in accordance with the 

Accomplishment Instructions, paragraph 

3.A., in Sikorsky Alert Service Bulletin (ASB) 

No. 76–55–20A, Revision A, dated November 

11, 2003 (No. 76–55–20A). For purposes of 

this AD, ASB No. 76–55–20A is applicable to 

Model S–76B helicopters as well as Model S– 

76A and S–76C helicopters. 

(1) If a crack, a loose or working fastener, 

or corrosion is found in the aft spar assembly, 

before further flight: 

(i) Repair or replace any unairworthy parts 

and 

(ii) Inspect the vertical stabilizer forward 

spar assembly (forward spar assembly) for a 

crack, a loose or working fastener, or 

corrosion in accordance with the 

Accomplishment Instructions, paragraph 

3.B., in ASB No. 76–55–20A. Contacting the 

manufacturer is not required by this AD. 

(2) If a crack, a loose or working fastener, 

or corrosion is found in the forward spar 

assembly, repair in accordance with the 

applicable maintenance manual or replace 

with airworthy parts before further flight. 

(b) Within 30 days, unless accomplished 

previously, and thereafter at intervals not to 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 176 / Monday, September 13, 2010 / Rules and Regulations 55455 

exceed 200 hours TIS, track-and-balance the 

tail rotor in accordance with the 

Accomplishment Instructions, paragraph 

3.A., in ASB No. 76–65–58A, Revision A, 

dated November 11, 2003. 

Note 1: Although the ASB specifies only an 

initial inspection of the aft spar assembly and 

a track and balance of the tail rotor, this AD 

requires inspecting the aft spar assembly and 

track-and-balancing the tail rotor repetitively. 

Note 2: The track-and-balancing of the tail 

rotor that is required by paragraph (b) of this 

AD involves both a pilot and mechanic. The 

pilot’s function is to operate the helicopter to 

a ‘‘light on wheels’’ state—almost to the point 

of takeoff. The mechanic is needed to 

accomplish the vibration measurements. 

(c) On or before December 31, 2010, install 

a vertical stabilizer modification kit, part 

number 76070–20562–011, 76070–20563– 

011, or 76070–20564–011. Installing the 

vertical stabilizer modification kit is 

terminating action for the requirements of 

this AD. 

(d) 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, Engine and Propeller 

Directorate, ATTN: Nicholas Faust, Aviation 

Safety Engineer, FAA, 12 New England 

Executive Park, Burlington, MA 01803, 

telephone (781) 238–7763, fax (781) 238– 

7170, for information about previously 

approved alternative methods of compliance. 

(e) The Joint Aircraft System/Component 

(JASC) Code 5530 is: Vertical Stabilizer. 

(f) The inspections and track-and-balance 

shall be done in accordance with the 

specified portions of Sikorsky Alert Service 

Bulletin No. 76–55–20A, Revision A, dated 

November 11, 2003, and Sikorsky Alert 

Service Bulletin No. 76–65–58A, Revision A, 

dated November 11, 2003. 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 Sikorsky Aircraft Corporation, 

Attn: Manager, Commercial Technical 

Support, mailstop s581a, 6900 Main Street, 

Stratford, Connecticut 06614, phone (203) 

383–4866, e-mail address 

tsslibrary@sikorsky.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. 

(g) This amendment becomes effective on 

October 18, 2010. 

Issued in Fort Worth, Texas, on August 12, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–21596 Filed 9–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0037; Directorate 

Identifier 2009–NM–240–AD; Amendment 

39–16431; AD 2010–19–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–700 (IGW) Series 

Airplanes Equipped With Auxiliary Fuel 

Tanks Installed in Accordance With 

Configuration 3 of Supplemental Type 

Certificate ST00936NY 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 737–700 (IGW) series airplanes. 

This AD requires deactivation or 

modification of PATS Aircraft, LLC, 

auxiliary fuel tanks. This AD results 

from fuel system reviews conducted by 

the manufacturer. We are issuing this 

AD to prevent the potential of ignition 

sources inside fuel tanks, which, in 

combination with flammable fuel 

vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: This AD is effective October 18, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 18, 2010. 

ADDRESSES: For service information 

identified in this AD, contact DeCrane 

Aerospace, PATS Aircraft Systems, 

21652 Nanticoke Avenue, Georgetown, 

Delaware 19947; telephone 302–253– 

6157; fax 302–855–0153; e-mail 

giuseppecoppola@ 

decraneaerospace.com; Internet 

http://www.decraneaerospace.com. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Mazdak Hobbi, Aerospace Engineer, 

Propulsion and Services Branch, ANE– 

173, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7330; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Model 737–700 (IGW) series 

airplanes. That NPRM was published in 

the Federal Register on February 12, 

2010 (75 FR 6865). That NPRM 

proposed to require deactivation or 

modification of PATS Aircraft, LLC, 

auxiliary fuel tanks. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Clarify Configuration 3 

Airplanes Affected 

Global Jet asks what has changed 

regarding Configuration 3 airplanes 

affected by the actions in the NPRM. 

Global Jet states that it received an email 

from the FAA in May 2008, which 

specified that no further action was 

required for its Configuration 3 

airplanes. Global Jet asks why it was in 

compliance with SFAR 88 last year and 

is not in compliance this year, although 

the airplane configuration has not 

changed in any way. PATS recommends 

clarifying that although Configuration 3 

airplanes were excluded from AD 2008– 

22–01, those airplanes are not in 

compliance with the SFAR 88 

regulations. 

We acknowledge the commenters’ 

concerns and provide the following 

clarification. We have received new 

information from a secondary review of 

Configuration 3 airplanes and have 

determined that they are not compliant 

with the SFAR 88 regulations. 

Therefore, those airplanes are included 

in the applicability of this AD. We have 

made no change to the AD in this 

regard. 

Request To Refer to AD 2008–22–01 

PATS Aircraft, LLC (PATS), asks that 

we include a reference to the 

requirements of AD 2008–22–01, 

amendment 39–15696 (73 FR 62872, 

October 22, 2008), in the NPRM. PATS 

states that the information specified in 

the NPRM corrects an error in AD 2008– 

22–01, which incorrectly identifies 

Configuration 3 airplanes as being 


srobinson on DSKHWCL6B1PROD with RULES