23382 Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations 

between the pipe and the RH rear half-wall 

may lead to rupture of the P3 air pipe (first 

section), which could cause an 

uncommanded power loss to flight idle. We 

are issuing this AD to prevent an 

uncommanded power loss to flight idle, 

which could result in an emergency 

autorotation landing or accident. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For installed engines, within 100 engine 

hours (EH) after the effective date of this AD: 

(i) Inspect the clearance between the P3 air 

pipe (first section) and the RH rear half-wall 

for sufficient clearance (0.5 mm or more). 

(ii) Use paragraph 2.B.(1) of Turbomeca 

Mandatory Service Bulletin (MSB) No. 319 

75 4810, Version B, dated January 25, 2011 

to do the inspection. 

(2) Thereafter, repeat the inspections in 

paragraphs (e)(1)(i) through (e)(1)(ii) of this 

AD as follows: 

(i) At every installation of a RH rear halfwall P/N 0 319 99 824 0 on an installed 

engine, and 

(ii) After every installation or reinstallation 

of an engine with a RH rear half-wall P/N 0 

319 99 824 0 installed. 

(3) If the P3 air pipe (first section) or the 

RH rear half-wall P/N 0 319 99 824 0 is found 

damaged, then before further flight, replace 

the damaged part(s) with parts eligible for 

installation. 

(4) If the P3 air pipe (first section) and the 

RH rear half-wall P/N 0 319 99 824 0 are 

found contacting each other but are not 

damaged, replace the RH rear half-wall with 

a RH rear half-wall eligible for installation. 

(5) If both the P3 air pipe (first section) and 

the RH rear half-wall are found not damaged 

during the inspections specified in paragraph 

(e)(1) or (e)(2) of this AD, and the clearance 

between them is less than 0.5 mm, but they 

are not contacting each other, then repeat the 

inspection in paragraphs (e)(1)(i) and 

(e)(1)(ii) of this AD within every 100 EH. 

(6) Installation of RH rear half-wall, P/N 0 

319 99 008 0, is terminating action to the 

inspections required by paragraphs (e)(1), 

(e)(2), and (e)(5) of this AD. 

(7) Once a RH rear half-wall, P/N 0 319 99 

008 0, is installed on an engine, do not install 

a RH rear half-wall, P/N 0 319 99 824 0, on 

that engine. 

(f) Definition 

For the purpose of this AD, parts eligible 

for installation is defined as: 

(1) An undamaged P3 air pipe (first 

section). 

(2) An undamaged RH rear half-wall P/N 

0 319 99 824 0. 

(3) A new design RH rear half-wall P/N 0 

319 99 008 0. 

(g) Credit for Previous Action 

An inspection performed on an installed 

engine before the effective date of this AD 

using Turbomeca MSB No. 319 75 4810, 

Version A, dated May 14, 2008, satisfies the 

inspection requirement in paragraphs (e)(1)(i) 

and (e)(1)(ii) of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve alternative methods of 

compliance for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Mark Riley, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7758; fax: 781–238–7199; 

email: mark.riley@faa.gov. 

(2) European Aviation Safety Agency AD 

2011–0182R1, dated February 3, 2012, 

pertains to the subject of this AD. 

(3) For service information identified in 

this AD, contact. You may review copies of 

the referenced service information at the 

FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(j) Material Incorporated by Reference 

You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information. 

(1) Turbomeca Mandatory Service Bulletin 

No. 319 75 4810, Version A, dated May 14, 

2008, approved for IBR August 19, 2009 (74 

FR 34221, July 15, 2009). 

(2) Turbomeca Mandatory Service Bulletin 

No. 319 75 4810, Version B, dated January 

25, 2011, approved for IBR May 24, 2012. 

(3) For service information identified in 

this AD, contact Turbomeca, 40220 Tarnos, 

France; telephone 33 (0)5 59 74 40 00; telex 

570 042; fax 33 (0)5 59 74 45 15. 

(4) You may review copies of the 

referenced service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

cfr/ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

April 3, 2012. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–8584 Filed 4–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1115; Directorate 

Identifier 2010–SW–011–AD; Amendment 

39–17017; AD 2012–08–01] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S–92A helicopters. This AD was 

prompted by the manufacturer’s 

analysis of engine data that revealed the 

data was inaccurate in dealing with 

available above specification engine 

power margin. This AD requires 

revising the Operating Limitations 

section of the Sikorsky Model S–92A 

Rotorcraft Flight Manual (RFM). The 

actions are intended to prevent the use 

of inaccurate engine performance data 

in calculating maximum gross weight by 

revising the Operating Limitations 

section of the RFM. 

DATES: This AD is effective May 24, 

2012. 

ADDRESSES: For service information 

identified in this 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 a 

copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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 AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 


srobinson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations 23383 

FOR FURTHER INFORMATION CONTACT: John 

Coffey, Aviation Safety Engineer, Boston 

Aircraft Certification Office, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7173; email 

john.coffey@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 26, 2011, at 76 FR 66207, 

the Federal Register published our 

Notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 to include an AD that would apply 

to Sikorsky Model S–92A helicopters, 

certificated in any category. That NPRM 

proposed to require revising the 

Operating Limitations section, Part 1, 

Section 1, Weight Limits, of the 

appropriate Sikorsky Model S–92A RFM 

with the following statement 

‘‘Performance credit for above 

specification engine power margin is 

prohibited.’’ The proposed requirements 

were intended to prevent the use of 

inaccurate performance data in 

calculating the maximum gross weight. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

Related Service Information 

Sikorsky has published various RFM 

revisions correcting the charts in Parts 

I and IV of the RFM. If those revisions 

have previously been incorporated into 

the RFM, the RFM revision specified by 

the NPRM would not be required. The 

RFM revisions, all dated April 9, 2008, 

are as follows: 

Affected RFM 

Revision 

with correct 

charts 

S92A–RFM–002 ........................ Revision 8. 

S92A–RFM–003 ........................ Revision 7. 

S92A–RFM–004 ........................ Revision 6. 

S92A–RFM–005 ........................ Revision 5. 

S92A–RFM–006 ........................ Revision 6. 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design and that air safety and 

the public interest require adopting the 

AD requirements as proposed, except 

for minor editorial and formatting 

changes. These changes will not 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

We estimate that this AD will affect 

37 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. It will take about 1 workhour per helicopter to insert the 

revisions into the RFM at an average 

labor rate of $85 per work-hour. Parts 

costs are not associated with this AD. 

Based on these figures, we estimate the 

total cost impact of this AD on U.S. 

operators to be $3,145. 

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 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2012–08–01 Sikorsky Aircraft Corporation: 

Amendment 39–17017; Docket No. 

FAA–2011–1115; Directorate Identifier 

2010–SW–011–AD. 

(a) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation (Sikorsky) Model S–92A 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

inaccurate above specification engine power 

margin data. This condition could result in 

the use of inaccurate engine performance 

data in calculating maximum gross weight. 

(c) Effective Date 

This AD becomes effective May 24, 2012. 

(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 

Within 90 days: 

(1) By making pen and ink changes, insert 

into the Operating Limitations section, Part 1, 

Section 1, Weight Limits, of Rotorcraft Flight 

Manuals (RFMs) SA S92A–RFM–002, –003, 

–004, –005, and –006 the following limitation 

‘‘Performance credit for above specification 

engine power margin is prohibited.’’ 

(2) If the RFM already contains the 

revisions appropriate for your helicopter as 

listed in the following Table 1, all dated 

April 9, 2008, with the correct performance 

charts, without the performance credit as 

depicted in the circled area of Figure 1 of this 

AD, the operating limitation required by 

paragraph (1) of this AD does not need to be 

inserted into the RFM. 

TABLE 1 

Affected RFM 

Revision 

with correct 

charts 

S92A–RFM–002 ........................ Revision 8. 


srobinson on DSK4SPTVN1PROD with RULES
23384 Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations 

TABLE 1—Continued 

Affected RFM 

Revision 

with correct 

charts 

S92A–RFM–003 ........................ Revision 7. 

S92A–RFM–004 ........................ Revision 6. 

TABLE 1—Continued 

Affected RFM 

Revision 

with correct 

charts 

S92A–RFM–005 ........................ Revision 5. 

S92A–RFM–006 ........................ Revision 6. 

Note to paragraph (e)(2) of this AD: 

Previous RFM revisions allowed for the use 

of above-specification engine power margin 

as depicted in the circled area of Figure 1 of 

this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

John Coffey, Aviation Safety Engineer, 

Boston Aircraft Certification Office, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7173; email 

john.coffey@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under 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) Additional Information 

Sikorsky Rotorcraft Flight Manuals SA 

S92A–RFM–002, Revision 8; –003, Revision 

7; –004, Revision 6; –005, Revision 5; and 

–006, Revision 6, all dated April 9, 2008, 

which are not incorporated by reference, 

contain additional information about the 

subject of this AD. For this service 

information, contact Sikorsky Aircraft 


srobinson on DSK4SPTVN1PROD with RULESEr19AP12.000</GPH>
Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations 23385 

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 a copy 

of this service information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7200, Engine (Turbine/Turboprop). 

Issued in Fort Worth, Texas, on April 9, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–9298 Filed 4–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1226; Directorate 

Identifier 2011–NM–006–AD; Amendment 

39–17001; AD 2012–06–20] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by a report that the fuel 

crossfeed valves cannot be controlled 

when only emergency electrical power 

is available, that an unwanted 

configuration of the indication logic for 

the fuel fire shutoff valve was 

introduced during production, and that 

current fuel crossfeed indications are 

based on selection by the flightcrew 

instead of actual position of the 

crossfeed valve actuators. This AD 

requires modifying the crossfeed valve 

control and power supply, the crossfeed 

indication logic and power supply, and 

the indication logic for the fuel fire 

shutoff valve; modifying the overhead 

panel; and for certain airplanes, 

modifying the transfer logic of the 

center wing fuel tank. We are issuing 

this AD to prevent failure of an in-flight 

engine re-light following a double 

engine flame-out event, which could 

result in loss of the airplane. 

DATES: This AD becomes effective May 

24, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 24, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

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 the specified products. That 

NPRM was published in the Federal 

Register on November 8, 2011 (76 FR 

69163). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A recent safety review revealed that the 

fuel crossfeed valves cannot be controlled 

when only emergency electrical power is 

available. 

This condition, if not corrected, could (in 

combination with other factors) prevent an 

in-flight engine re-light following a double 

engine flame-out event, possibly resulting in 

loss of the aeroplane. 

Another review revealed that an unwanted 

configuration of the fuel fire shut-off valve 

indication logic had been introduced during 

production on a limited number of F28 Mark 

0100 aeroplanes. 

Furthermore, most of the current fuel 

crossfeed indications are based on the 

crossfeed selection made by the flight crew 

and not on the actual positions of the 

crossfeed valve actuators. In combination 

with other factors, the current crossfeed 

indications may mislead flight crews, 

possibly resulting in single engine in-flight 

shutdowns and/or unnecessary precautionary 

landings. 

For the reasons described above, this 

[EASA] AD requires modifications of the 

crossfeed valve control and power supply, of 

the crossfeed indication logic and power 

supply and of the fuel fire shut-off valve 

indication logic. 

* * * * * 

Required actions also include modifying 

the overhead panel (introducing 

provisions for a modified crossfeed 

indication), and, for certain airplanes, 

modifying the transfer logic of the 

center wing fuel tank. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 69163, November 8, 2011) or on the 

determination of the cost to the public. 

Explanation of Changes Made to This 

AD 

We have revised the heading for and 

the wording in paragraph (i) of this AD; 

this change has not changed the intent 

of that paragraph. We have also revised 

the document citations throughout this 

AD to more clearly identify the 

documents and their attachments. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

69163, November 8, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 69163, 

November 8, 2011). 

Costs of Compliance 

We estimate that this AD will affect 6 

products of U.S. registry. We also 

estimate that it will take about 86 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $4,180 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$68,940, or $11,490 per product. 

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 


srobinson on DSK4SPTVN1PROD with RULES