### 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.


### 23383 Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations

**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 complywith 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.


### 23384 Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations

T ABLE 

### 1—Continued

Affected RFM Revision with correct

charts

S92A–RFM–003 ........................ Revision 7. S92A–RFM–004 ........................ Revision 6. 

### T ABLE 

### 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


### 23385 Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations

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 alsoestimate 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