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

28439 

Vol. 74, No. 114 

Tuesday, June 16, 2009 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0518; Directorate 

Identifier 2009–SW–22–AD; Amendment 39– 

15940; AD 2009–13–01] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S–92A 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for Sikorsky Aircraft Corporation 

(Sikorsky) Model S–92A helicopters. 

That AD currently requires removing all 

main gearbox (MGB) filter bowl 

assembly mounting titanium studs 

(titanium studs) and replacing them 

with steel studs. This amendment 

requires the same actions as the existing 

AD as well as changes to the Rotorcraft 

Flight Manual (RFM). This amendment 

is prompted by an accident, by recent 

RFM changes made by the manufacturer 

that were not available when we issued 

the existing AD, and by our 

determination that certain MGB Normal 

and Emergency procedures in the RFM 

are unclear, may cause confusion, and 

may mislead the crew regarding MGB 

malfunctions, in particular the urgency 

to land immediately after warning 

indications of loss of MGB oil pressure 

and oil pressure below 5 pounds per 

square inch (psi). 

Replacing the titanium studs is 

intended to prevent their failure, which 

could result in rapid loss of oil, failure 

of the MGB, and subsequent loss of 

control of the helicopter. Changing the 

RFM procedures is intended to clarify 

and emphasize certain Normal and 

Emergency procedures to give the crew 

the best available information in the 

event of certain MGB malfunctions. 

DATES: Effective July 1, 2009. 

The incorporation by reference of 

Sikorsky Alert Service Bulletin No. 92– 

63–014, Revision A, dated March 20, 

2009, was approved previously for 

incorporation by reference by the 

Director of the Federal Register on April 

27, 2009 (74 FR 18977, April 27, 2009). 

Comments for inclusion in the Rules 

Docket must be received on or before 

August 17, 2009. 

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: John 

M. Coffey, Flight Test Engineer, FAA, 12 

New England Executive Park, 

Burlington, MA 01803, telephone (781) 

238–7173, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: On March 

23, 2009, we issued Emergency AD 

2009–07–53 for Sikorsky Model S–92A 

helicopters, which requires, before 

further flight, removing all titanium 

studs that attach the MGB filter bowl 

assembly to the MGB and replacing 

them with steel studs. That action was 

prompted by the failure of 2 studs that 

were found broken during a fatal 

accident investigation in Canada. Before 

the accident, the manufacturer was 

investigating a July 2008 incident that 

also involved broken studs. In both 

cases, the broken studs resulted in rapid 

loss of MGB oil. The failures have been 

tied to fretting and galling of the original 

titanium studs. That emergency AD was 

published as Amendment 39–15886 on 

April 27, 2009 (74 FR 18977). This AD 

continues to require removing all 

titanium studs and replacing them with 

steel studs. 

Since the fatal accident and since 

issuing AD 2009–07–53, Sikorsky has 

issued revisions to the Normal and 

Emergency procedures of the RFM. We 

have determined that these revisions are 

necessary because the existing 

procedures are unclear, may cause 

confusion, and may mislead the crew 

regarding MGB malfunctions, in 

particular the urgency to land 

immediately after warning indications 

of loss of MGB oil pressure and oil 

pressure below 5 psi. This action does 

not mandate the procedures the pilot 

must perform in an emergency, but 

requires making changes to the RFM to 

clarify and emphasize the Normal and 

Emergency procedures addressing 

specified MGB malfunctions, thus 

giving the pilot the necessary 

information to make an informed 

decision. We are superseding the 

existing AD to include the most recent 

RFM revisions because the revisions 

were not available when we originally 

issued AD 2009–07–53. 

We have reviewed Sikorsky Alert 

Service Bulletin No. 92–63–014A, 

Revision A, dated March 20, 2009 

(ASB), which describes procedures for 

removing titanium studs and replacing 

them with steel suds. We have also 

reviewed the RFM revisions and, after 

full coordination with Sikorsky, 

approved them on May 13, 2009. 

Sikorsky has since assured us that they 

have provided the revised RFM 

procedures to all affected operators. The 

RFM revisions are as follows: 


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28440 Federal Register / Vol. 74, No. 114 / Tuesday, June 16, 2009 / Rules and Regulations 

• SA S92A–RFM–000 Revision No. 4, 

• SA S92A–RFM–002 Revision No. 

10, 

• SA S92A–RFM–003 Revision No. 

10, 

• SA S92A–RFM–004 Revision No. 8, 

• SA S92A–RFM–005 Revision No. 7, 

• SA S92A–RFM–006 Revision No. 8, 

and 

• S92A–RFM Supplement No. 3, 

Revision No. 2. 

In addition to the RFM revisions, we 

have also reviewed associated Errata 

Sheets, dated June 4, 2009, that provide 

corrections to those RFM revisions; 

however, we are not mandating that 

they be incorporated. 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other Sikorsky Model S–92A 

helicopters of the same type design, this 

AD supersedes AD 2009–07–53 to 

require, before further flight, removing 

all titanium studs and replacing them 

with steel studs. These actions must be 

accomplished by following the specified 

portions of the ASB described 

previously. Because the critical unsafe 

condition can adversely affect the 

structural integrity and controllability of 

the helicopter, AD 2009–07–53 remains 

in full effect until the effective date of 

this AD. 

Making the Normal and Emergency 

RFM revisions that were not available 

when we issued AD 2009–07–53 is 

required within 10 hours time-inservice. The short compliance time is 

required because certain procedures in 

the existing RFM may be misleading, 

presenting an unacceptable level of risk, 

and because the required RFM revisions 

are already approved by the FAA and 

available to operators, imposing a 

minimal burden. Therefore, it is found 

that notice and opportunity for prior 

public comment hereon are unnecessary 

and contrary to the public interest, and 

that good cause also exists for making 

this amendment effective in less than 30 

days. 

We estimate that this AD will affect 

35 helicopters of U.S. registry. 

Replacing the studs will take 

approximately 6 work hours per 

helicopter to accomplish at an average 

labor rate of $80 per work hour. In 

accordance with the ASB, required parts 

and tooling are available at no cost. 

Making the changes to the RFM will 

take a minimal amount of time and cost. 

Based on these figures, we estimate the 

total cost impact of the AD on U.S. 

operators to be $16,800, assuming there 

are no parts and tooling costs. 

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–2009–0518; 

Directorate Identifier 2009–SW–22–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 

removing Amendment 39–15886 (74 FR 

18977, April 27, 2009), and by adding 

a new airworthiness directive (AD), 

Amendment 39–15940, to read as 

follows: 

2009–13–01 Sikorsky Aircraft Corporation: 

Amendment 39–15940. Docket No. 

FAA–2009–0518; Directorate Identifier 

2009–SW–22–AD. Supersedes AD 2009– 

07–53, Amendment 39–15886, Docket 

No. FAA–2009–0351, Directorate 

Identifier 2009–SW–08–AD. 

Applicability: Model S–92A helicopters, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of a main gearbox (MGB) 

filter bowl assembly mounting titanium stud 

(titanium stud), which could result in rapid 

loss of oil, failure of the MGB, and 

subsequent loss of control of the helicopter; 

and to clarify and emphasize certain Normal 

and Emergency procedures to give the crew 

the best available information in the event of 

certain MGB malfunctions, accomplish the 

following: 

(a) Before further flight, for all Model S– 

92A helicopters with a MGB housing 

assembly, part number (P/N) 92351–15110– 

042, –043, or –044, that is not marked with 

‘‘TS–062–01’’ near the P/N: 

(1) Remove the titanium studs by following 

the Accomplishment Instructions in Sikorsky 

Alert Service Bulletin No. 92–63–014, Rev. 


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Federal Register / Vol. 74, No. 114 / Tuesday, June 16, 2009 / Rules and Regulations 28441 

A, dated March 20, 2009 (ASB), paragraph 

3.A. 

Note 1: Figure 1 of the ASB contains 

guidance for removal and installation of the 

studs 

(2) Visually inspect the tapped holes and 

the MGB housing lockring counterbore for 

damage. If you find damage in the tapped 

holes or in the MGB housing lockring 

counterbore, contact the Boston Aircraft 

Certification Office for an approved repair. 

(3) Install steel studs and mark the MGB 

housing as ‘‘TS–062–01’’ near the P/N by 

following the Accomplishment Instructions 

in the ASB, paragraph 3.C. 

(b) Within 10 hours time-in-service, for all 

helicopters regardless of MGB housing 

assembly P/N: 

(1) Revise the Normal and Emergency 

procedures sections of the Rotorcraft Flight 

Manual (RFM) by making the following 

changes, approved May 13, 2009: 

RFM Remove Remove Insert 

SA S92A–RFM–000 

Part I.

Temporary Revision (T-Rev) No. 

1, Revised Main Gearbox 

Emergency Procedure.

Page 2–12, and Sub-Section 7 

‘‘Gear Box Malfunctions’’ from 

Section III.

Page 2–12, and Sub-Section 7 ‘‘Gear Box 

Malfunctions’’ from Section III of SA S92A– 

RFM–000, Revision No. 4. 

SA S92A–RFM–002 

Part I.

T-Rev No. 5, Revised Main Gearbox Emergency Procedure.Page 2–13, and Sub-Section 7 

‘‘Gear Box Malfunctions’’ from 

Section III.

Page 2–13, and Sub-Section 7 ‘‘Gear Box 

Malfunctions’’ from Section III of SA S92A– 

RFM–002, Revision No. 10. 

SA S92A–RFM–003 

Part I.

T-Rev No. 4, Revised Main Gearbox Emergency Procedure.Page 2–13, and Sub-Section 7 

‘‘Gear Box Malfunctions’’ from 

Section III.

Page 2–13, and Sub-Section 7 ‘‘Gear Box 

Malfunctions’’ from Section III of SA S92A– 

RFM–003, Revision No. 10. 

SA S92A–RFM–004 

Part I.

T-Rev No. 4, Revised Main Gearbox Emergency Procedure.Page 2–12, and Sub-Section 7 

‘‘Gear Box Malfunctions’’ from 

Section III.

Page 2–12, and Sub-Section 7 ‘‘Gear Box 

Malfunctions’’ from Section III of SA S92A– 

RFM–004, Revision No. 8. 

SA S92A–RFM–005 

Part I.

T-Rev No. 3, Revised Main Gearbox Emergency Procedure.Page 2–13, and Sub-Section 7 

‘‘Gear Box Malfunctions’’ from 

Section III.

Page 2–13, and Sub-Section 7 ‘‘Gear Box 

Malfunctions’’ from Section III of SA S92A– 

RFM–005, Revision No. 7. 

SA S92A–RFM–006 

Part I.

T-Rev No. 2, Revised Main Gearbox Emergency Procedure.Page 2–13, and Sub-Section 7 

‘‘Gear Box Malfunctions’’ from 

Section III.

Page 2–13, and Sub-Section 7 ‘‘Gear Box 

Malfunctions’’ from Section III of SA S92A– 

RFM–006, Revision No. 8. 

S92A–RFMS No. 3 ...... N/A ................................................ Sub-Section 7 ‘‘Gear Box Malfunctions’’ from Section III.Sub-Section 7 ‘‘Gear Box Malfunctions’’ from 

Section III of S92A-RFM Supplement No. 

3, Revision No. 2. 

All paragraphs of subsection 7 ‘‘Gear Box Malfunctions’’ starting with paragraph 7.0 are affected. 

Note 2: Inserting the following revisions, 

approved on May 13, 2009, and their 

associated Errata Sheets, dated June 4, 2009, 

into the RFM, as applicable, satisfies the 

requirements of this AD: 

(i) SA S92A–RFM–000 Revision No. 4, 

(ii) SA S92A–RFM–002 Revision No. 10, 

(iii) SA S92A–RFM–003 Revision No. 10, 

(iv) SA S92A–RFM–004 Revision No. 8, 

(v) SA S92A–RFM–005 Revision No. 7, 

(vi) SA S92A–RFM–006 Revision No. 8, 

and 

(vii) S92A–RFM Supplement No. 3, 

Revision No. 2. 

(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: John M. 

Coffey, FAA, 12 New England Executive 

Park, Burlington, MA 01803, telephone (781) 

238–7173, fax (781) 238–7170, for 

information about previously approved 

alternative methods of compliance. 

(d) Special flight permits will not be 

issued. 

(e) Remove and replace the titanium studs 

by following the specified portions of 

Sikorsky Alert Service Bulletin No. 92–63– 

014, Revision A, dated March 20, 2009. The 

Director of the Federal Register previously 

approved the incorporation by reference of 

this information on April 27, 2009 under 5 

U.S.C. 552(a) and 1 CFR part 51 (74 FR 

18977, April 27, 2009. Copies may be 

obtained from Sikorsky Aircraft Corporation, 

Attn: Manager, Commercial Technical 

Support, mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (203) 383–4866, email address tsslibrary@sikorsky.com or at 

http://www.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. 

(f) This amendment becomes effective on 

July 1, 2009. 

Issued in Fort Worth, Texas, on June 9, 

2009. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–14081 Filed 6–15–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Highway Administration 

23 CFR Parts 192, 470, 625, 634, 650, 

655, 772, 971, 972, 973, 1206, 1208, 

1210, and 1215 

[FHWA Docket No. FHWA–2009–0028] 

RIN 2125–AF30 

Address Correction 

AGENCY: Federal Highway 

Administration (FHWA), DOT. 

ACTION: Final rule. 

SUMMARY: The FHWA is amending a 

number of its regulations to reflect the 

move of DOT’s headquarters site in 

Washington, DC. 

DATES: Effective Date: June 16, 2009. 

FOR FURTHER INFORMATION CONTACT: 

Jennifer Outhouse, Office of Chief 

Counsel, 1200 New Jersey Avenue, SE., 

Washington, DC 20590; (202) 366–1381. 

SUPPLEMENTARY INFORMATION: This 

publication makes corrections to the 

FHWA regulations to update the DOT 

headquarters address. Since this 

amendment relates to departmental 

management, organization, procedure, 

and practice, notice and comment are 

unnecessary under 5 U.S.C. 553(b). 

Further, since the amendment merely 

makes technical corrections and 

updates, the FHWA finds good cause 

under 5 U.S.C. 553(d)(3) for the final 

rule to be effective on the date of 

publication in the Federal Register. 

Regulatory Analyses and Notices 

A. Executive Order 12866 and DOT 

Regulatory Policies and Procedures 

This final rule is not considered a 

significant regulatory action under 

Executive Order 12866 and DOT 

regulatory Policies and Procedures (44 

FR 11034). It was not reviewed by the 

Office of Management and Budget. 

There are no costs associated with this 

rule. 


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