Airworthiness Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E Airplanes, 65493-65496 [E9-29457]

Download as PDF Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Proposed Rules • We refer to the compliance time as ‘‘hours time-in-service’’ rather than ‘‘flying hours’’ and • We do not require returning spares to the manufacturer. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. Costs of Compliance Air transportation, Aircraft, Aviation safety, Safety. We estimate that this proposed AD would affect about 96 helicopters of U.S. registry. We also estimate that it would take about 2 work-hours per helicopter to do the proposed actions. The average labor rate is $80 per workhour. Required parts would cost about $8,335 per helicopter. Based on these figures, we estimate the cost of the proposed AD on U.S. operators would be $815,520, or $8,495 per helicopter, assuming that the drive shaft is replaced on each helicopter. Authority for This Rulemaking mstockstill on DSKH9S0YB1PROD with PROPOSALS 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. Therefore, I certify this proposed AD: 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. 17:17 Dec 09, 2009 Jkt 220001 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 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 product(s) identified in this rulemaking action. VerDate Nov<24>2008 List of Subjects in 14 CFR Part 39 [Amended] 65493 airworthy drive shaft that is not included in the applicability of this AD. Differences Between This AD and the MCAI AD (f) This AD differs from the MCAI AD as follows: (1) We refer to the compliance time as ‘‘hours time-in-service’’ rather than ‘‘flying hours’’ and (2) We do not require returning spares to the manufacturer. Other Information (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, ATTN: Uday Garadi, Aviation Safety Engineer, Regulations and Guidance Group, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5123, fax (817) 222– 5961, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Eurocopter France: Docket No. FAA–2009– 1090; Directorate Identifier 2009–SW– 31–AD. Related Information (h) European Aviation Safety Agency (EASA) AD No. 2006–0100, dated April 24, 2006, and Eurocopter Alert Service Bulletin No. 01.00.51, Revision 1, dated February 9, 2006, contain related information. Comments Due Date (a) We must receive your comments by January 11, 2010. Joint Aircraft System/Component (JASC) Code (i) JASC Code 6510: Tail rotor drive shaft. Other Affected ADs (b) None. Issued in Fort Worth, Texas on November 23, 2009. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E9–29431 Filed 12–9–09; 8:45 am] 2. The FAA amends § 39.13 by adding the following new AD: Applicability (c) This AD applies to Model AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters with tail rotor drive shaft forward shaft section, part number 355A 34–1090–00, serial number 858 through 873 (inclusive) with a prefix ‘‘M,’’ certificated in any category. This AD does not apply to helicopters manufactured after January 1, 2005. Reason (d) The mandatory continuing airworthiness information (MCAI) AD states that a metallurgical non-conformity was discovered on a flange of the forward shaft section of the tail rotor drive shaft (drive shaft). The MCAI AD also states that stress analysis has shown that this non-conformity can significantly reduce the strength of the drive shaft and thereby its service life. This AD is intended to remove non-conforming drive shafts from service and prevent failure of the drive shaft and subsequent loss of control of the helicopter. Actions and Compliance (e) Unless already accomplished, do the following: (1) For any drive shaft that has less than 2,400 hours time-in-service (TIS), on or before reaching 2,500 hours TIS, remove the drive shaft and replace it with an airworthy drive shaft that is not included in the applicability of this AD. (2) For any drive shaft with 2,400 or more hours TIS, within the next 100 hours TIS, remove the drive shaft and replace it with an PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1158; Directorate Identifier 2009–CE–063–AD] RIN 2120–AA64 Airworthiness Directives; PILATUS AIRCRAFT LTD. Model PC–12/47E Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an E:\FR\FM\10DEP1.SGM 10DEP1 65494 Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Proposed Rules Comments Invited aviation product. The MCAI describes the unsafe condition as: Field reports have indicated that the possibility exists that both Primary Flight Displays (PFDs) could indicate a roll attitude offset of up to 10 degrees in the same direction if an accelerated turn onto the active runway is performed immediately followed by take-off. In addition, annunciated heading splits have been reported. This condition has been reported to correct itself after several minutes. Additionally, if the aeroplane is operating in geographical latitudes with low horizontal magnetic field strength, incorrect heading may be displayed if the ADAHRS switches from GPS track to magnetometer heading while the aeroplane is on the ground. This situation, if not corrected, could result in an undesired bank angle, heading splits and/or incorrect heading, which would constitute an unsafe condition. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by January 25, 2010. ADDRESSES: You may send comments by any of the following methods: • 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. mstockstill on DSKH9S0YB1PROD with PROPOSALS 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: VerDate Nov<24>2008 17:17 Dec 09, 2009 Jkt 220001 We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–1158; Directorate Identifier 2009–CE–063–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On April 8, 2009, we issued AD 2009– 08–10, Amendment 39–15883 (74 FR 17384, April 15, 2009). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2009–08–10, an updated air data, attitude, and heading reference system version with improved software was developed. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No.: 2009– 0249, dated November 20, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Field reports have indicated that the possibility exists that both Primary Flight Displays (PFDs) could indicate a roll attitude offset of up to 10 degrees in the same direction if an accelerated turn onto the active runway is performed immediately followed by take-off. In addition, annunciated heading splits have been reported. This condition has been reported to correct itself after several minutes. Additionally, if the aeroplane is operating in geographical latitudes with low horizontal magnetic field strength, incorrect heading may be displayed if the ADAHRS switches from GPS track to magnetometer heading while the aeroplane is on the ground. This situation, if not corrected, could result in an undesired bank angle, heading splits and/or incorrect heading, which would constitute an unsafe condition. As a short-term interim measure, AD 2009– 0028–E has been released in February 2009 to limit at 30° the bank angle during climb. Afterwards, as a result of the ongoing investigation, the problem has been temporarily addressed with some limitations in the take-off procedure. These limitations PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 have been mandated by AD 2009–0080–E which superseded AD 2009–0028–E. In order to terminate the operational limitations, an updated ADAHRS version with improved software was developed. For the reasons described above this AD supersedes AD 2009–0080–E and mandates as a terminating action either an update of the ADAHRS software or the replacement of the ADAHRS unit. From MSN 1181 and subsequent an improved ADAHRS unit was implemented during production. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information PILATUS AIRCRAFT LTD. has issued PILATUS PC–12 Service Bulletin No: 34–022, dated October 5, 2009. Honeywell International Inc. has issued Service Bulletin KSG 7200–34–09, Revision 0, dated September 24, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance We estimate that this proposed AD will affect 50 products of U.S. registry. We also estimate that it would take about 6 work-hours per product to E:\FR\FM\10DEP1.SGM 10DEP1 Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Proposed Rules comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $0 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 costs. 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 the proposed AD on U.S. operators to be $24,000, or $480 per product. Authority for This Rulemaking 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 Regulatory Findings mstockstill on DSKH9S0YB1PROD with PROPOSALS 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. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Field reports have indicated that the possibility exists that both Primary Flight Displays (PFDs) could indicate a roll attitude offset of up to 10 degrees in the same direction if an accelerated turn onto the active runway is performed immediately followed by take-off. In addition, annunciated heading splits have been reported. This condition has been reported to correct itself after several minutes. Additionally, if the aeroplane is operating in geographical latitudes with low horizontal magnetic field strength, incorrect heading may be displayed if the ADAHRS switches from GPS track to magnetometer heading while the aeroplane is on the ground. This situation, if not corrected, could result in an undesired bank angle, heading splits and/or incorrect heading, which would constitute an unsafe condition. As a short-term interim measure, AD 2009– 0028–E has been released in February 2009 to limit at 30° the bank angle during climb. Afterwards, as a result of the ongoing investigation, the problem has been temporarily addressed with some limitations in the take-off procedure. These limitations 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 above, 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); 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 a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. VerDate Nov<24>2008 17:17 Dec 09, 2009 Jkt 220001 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15883 (74 FR 17384, April 15, 2009), and adding the following new AD: PILATUS AIRCRAFT LTD.: Docket No. FAA–2009–1158; Directorate Identifier 2009–CE–063–AD. Comments Due Date (a) We must receive comments by January 25, 2010. Affected ADs (b) This AD supersedes AD 2009–08–10, Amendment 39–15883. Applicability (c) This AD applies to Models PC–12/47E airplanes, all manufacturer serial numbers (MSN), certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 34: Navigation. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 65495 have been mandated by AD 2009–0080–E which superseded AD 2009–0028–E. In order to terminate the operational limitations, an updated ADAHRS version with improved software was developed. For the reasons described above this AD supersedes AD 2009–0080–E and mandates as a terminating action either an update of the ADAHRS software or the replacement of the ADAHRS unit. From MSN 1181 and subsequent an improved ADAHRS unit was implemented during production. Actions and Compliance (f) Unless already done, do the following actions: (1) For MSN 545 and MSN 1001 through MSN 1180, before further flight after April 20, 2009 (the effective date of AD 2009–08– 10), incorporate PILATUS AIRCRAFT LTD. Temporary Revision No. 11 to PC–12/47E Pilot’s Operating Handbook (POH), Report No. 02277, dated March 18, 2009, into the Pilatus PC–12/47E POH. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations 14 CFR 43.7 may do this action. Make an entry in the aircraft records showing compliance with this portion of the AD following 14 CFR 43.9. (2) For MSN 545 and MSN 1001 through MSN 1180, within 180 days after the effective date of this AD: (i) Update the air data, attitude, and heading reference system (ADAHRS) software following the accomplishment instructions of Honeywell International Inc. Service Bulletin KSG 7200–34–09, Revision 0, dated September 24, 2009; or (ii) Replace ADAHRS unit KSG 7200 Honeywell Part Number (P/N) 065–00188– 5102, Software Version MOD 02/02 (Pilatus P/N 985.99.12.192) with a new ADAHRS unit with Honeywell P/N 065–00188–5103 (Pilatus P/N 985.99.12.205) following the accomplishment instructions of PILATUS AIRCRAFT LTD. PILATUS PC–12 Service Bulletin No: 34–022, dated October 5, 2009. (3) For MSN 545 and 1001 through 1180, before further flight after the actions required by paragraph (f)(2) of this AD, remove PILATUS AIRCRAFT LTD. Temporary Revision No. 11 to PC–12/47E Pilot’s Operating Handbook, Report No. 02277, dated March 18, 2009. (4) Do not install an ADAHRS unit with Honeywell P/N 065–00188–5102 (Pilatus P/N 985.99.12.192) on any affected Model PC–12/47E airplane, as follows: (i) For MSN 545 and 1001 through 1180 airplanes, as of 180 days after the effective date of this AD; and (ii) For all other MSNs, as of the effective date of this AD. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, E:\FR\FM\10DEP1.SGM 10DEP1 65496 Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Proposed Rules FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2009–0249, dated November 20, 2009, PILATUS AIRCRAFT LTD. Temporary Revision No. 11 to PC–12/47E Pilot’s Operating Handbook, Report No. 02277, dated March 18, 2009; Honeywell International Inc. Service Bulletin KSG 7200–34–09, Revision 0, dated September 24, 2009; and PILATUS AIRCRAFT LTD. PILATUS PC–12 Service Bulletin No: 34–022, dated October 5, 2009, for related information. Issued in Kansas City, Missouri, on December 4, 2009. William Timberlake, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–29457 Filed 12–9–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1088; Directorate Identifier 2008–SW–76–AD] mstockstill on DSKH9S0YB1PROD with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model S–92A Helicopters AGENCY: Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: This document proposes adopting a new airworthiness directive VerDate Nov<24>2008 17:17 Dec 09, 2009 Jkt 220001 (AD) for the Sikorsky Model S–92A helicopters. The AD would require revising the Rotorcraft Flight Manual (RFM), Operating Limitations section, to make it clear to operators that this model helicopter was not certificated to the standards that allow for the carriage of human external cargo. This proposal is prompted by a mistake in the RFM, which allows ‘‘Class D’’ rotorcraft load combinations for human external cargo load (HEC) operations for this model. The Model S–92A RFM does not include the required one-engine inoperative (OEI) hover performance and procedures. The actions specified by the proposed AD are intended to correct the Limitations section of the RFM to prevent HEC operations, which could result in injury or loss of life. DATES: Comments must be received on or before February 8, 2010. ADDRESSES: Use one of the following addresses to submit comments on this proposed 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 proposed 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. FOR FURTHER INFORMATION CONTACT: John Coffey, Flight Test Engineer, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7173, fax (781) 238–7170. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2009–1088, Directorate Identifier 2008–SW–76–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed 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 proposed rulemaking. 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 or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000. Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information 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. Discussion This document proposes adopting a new AD for the Sikorsky Model S–92A helicopters. The AD would require revising the RFM SA S92A–RFM–003, Part 1, Section 1, Operating Limitations, Types of Operation, by removing the statement ‘‘RESCUE HOIST: Category ‘A’ only External load operations with Class ‘D’ external loads.’’ The AD would require replacing that statement with ‘‘HOIST: Class D external loads PROHIBITED.’’ Also, the AD would require revising the RFM by removing all instances of the terms ‘‘RESCUE HOIST’’ and replacing them with the term ‘‘HOIST.’’ This proposal is prompted by a review of the RFM, in which a mistake was discovered. The RFM states that ‘‘Class D’’ external loads are approved for external load operations for this model. However, the Model S–92A does not comply with the requirements of 14 CFR 29.865(c)(6) because, for HEC applications requiring use of Category A rotorcraft, that rotorcraft must have OEI hover performance and procedures in the RFM for the weights, altitudes and temperatures for which that external load approval is requested. The Model E:\FR\FM\10DEP1.SGM 10DEP1

Agencies

[Federal Register Volume 74, Number 236 (Thursday, December 10, 2009)]
[Proposed Rules]
[Pages 65493-65496]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29457]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1158; Directorate Identifier 2009-CE-063-AD]
RIN 2120-AA64


Airworthiness Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an

[[Page 65494]]

aviation product. The MCAI describes the unsafe condition as:

    Field reports have indicated that the possibility exists that 
both Primary Flight Displays (PFDs) could indicate a roll attitude 
offset of up to 10 degrees in the same direction if an accelerated 
turn onto the active runway is performed immediately followed by 
take-off. In addition, annunciated heading splits have been 
reported. This condition has been reported to correct itself after 
several minutes.
    Additionally, if the aeroplane is operating in geographical 
latitudes with low horizontal magnetic field strength, incorrect 
heading may be displayed if the ADAHRS switches from GPS track to 
magnetometer heading while the aeroplane is on the ground.
    This situation, if not corrected, could result in an undesired 
bank angle, heading splits and/or incorrect heading, which would 
constitute an unsafe condition.

    The proposed AD would require actions that are intended to address 
the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by January 25, 
2010.

ADDRESSES: You may send comments by any of the following methods:
     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.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket 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: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-1158; 
Directorate Identifier 2009-CE-063-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On April 8, 2009, we issued AD 2009-08-10, Amendment 39-15883 (74 
FR 17384, April 15, 2009). That AD required actions intended to address 
an unsafe condition on the products listed above.
    Since we issued AD 2009-08-10, an updated air data, attitude, and 
heading reference system version with improved software was developed.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No.: 2009-0249, dated November 20, 2009 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Field reports have indicated that the possibility exists that 
both Primary Flight Displays (PFDs) could indicate a roll attitude 
offset of up to 10 degrees in the same direction if an accelerated 
turn onto the active runway is performed immediately followed by 
take-off. In addition, annunciated heading splits have been 
reported. This condition has been reported to correct itself after 
several minutes.
    Additionally, if the aeroplane is operating in geographical 
latitudes with low horizontal magnetic field strength, incorrect 
heading may be displayed if the ADAHRS switches from GPS track to 
magnetometer heading while the aeroplane is on the ground.
    This situation, if not corrected, could result in an undesired 
bank angle, heading splits and/or incorrect heading, which would 
constitute an unsafe condition.
    As a short-term interim measure, AD 2009-0028-E has been 
released in February 2009 to limit at 30[deg] the bank angle during 
climb. Afterwards, as a result of the ongoing investigation, the 
problem has been temporarily addressed with some limitations in the 
take-off procedure. These limitations have been mandated by AD 2009-
0080-E which superseded AD 2009-0028-E.
    In order to terminate the operational limitations, an updated 
ADAHRS version with improved software was developed.
    For the reasons described above this AD supersedes AD 2009-0080-
E and mandates as a terminating action either an update of the 
ADAHRS software or the replacement of the ADAHRS unit. From MSN 1181 
and subsequent an improved ADAHRS unit was implemented during 
production.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    PILATUS AIRCRAFT LTD. has issued PILATUS PC-12 Service Bulletin No: 
34-022, dated October 5, 2009. Honeywell International Inc. has issued 
Service Bulletin KSG 7200-34-09, Revision 0, dated September 24, 2009. 
The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 50 products of U.S. 
registry. We also estimate that it would take about 6 work-hours per 
product to

[[Page 65495]]

comply with the basic requirements of this proposed AD. The average 
labor rate is $80 per work-hour. Required parts would cost about $0 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 costs. 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 the proposed AD on 
U.S. operators to be $24,000, or $480 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 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 above, 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); 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 a regulatory 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-15883 (74 FR 
17384, April 15, 2009), and adding the following new AD:

PILATUS AIRCRAFT LTD.: Docket No. FAA-2009-1158; Directorate 
Identifier 2009-CE-063-AD.

Comments Due Date

    (a) We must receive comments by January 25, 2010.

Affected ADs

    (b) This AD supersedes AD 2009-08-10, Amendment 39-15883.

Applicability

    (c) This AD applies to Models PC-12/47E airplanes, all 
manufacturer serial numbers (MSN), certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 34: 
Navigation.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Field reports have indicated that the possibility exists that 
both Primary Flight Displays (PFDs) could indicate a roll attitude 
offset of up to 10 degrees in the same direction if an accelerated 
turn onto the active runway is performed immediately followed by 
take-off. In addition, annunciated heading splits have been 
reported. This condition has been reported to correct itself after 
several minutes.
    Additionally, if the aeroplane is operating in geographical 
latitudes with low horizontal magnetic field strength, incorrect 
heading may be displayed if the ADAHRS switches from GPS track to 
magnetometer heading while the aeroplane is on the ground.
    This situation, if not corrected, could result in an undesired 
bank angle, heading splits and/or incorrect heading, which would 
constitute an unsafe condition.
    As a short-term interim measure, AD 2009-0028-E has been 
released in February 2009 to limit at 30[deg] the bank angle during 
climb. Afterwards, as a result of the ongoing investigation, the 
problem has been temporarily addressed with some limitations in the 
take-off procedure. These limitations have been mandated by AD 2009-
0080-E which superseded AD 2009-0028-E.
    In order to terminate the operational limitations, an updated 
ADAHRS version with improved software was developed.
    For the reasons described above this AD supersedes AD 2009-0080-
E and mandates as a terminating action either an update of the 
ADAHRS software or the replacement of the ADAHRS unit.
    From MSN 1181 and subsequent an improved ADAHRS unit was 
implemented during production.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) For MSN 545 and MSN 1001 through MSN 1180, before further 
flight after April 20, 2009 (the effective date of AD 2009-08-10), 
incorporate PILATUS AIRCRAFT LTD. Temporary Revision No. 11 to PC-
12/47E Pilot's Operating Handbook (POH), Report No. 02277, dated 
March 18, 2009, into the Pilatus PC-12/47E POH. The owner/operator 
holding at least a private pilot certificate as authorized by 
section 43.7 of the Federal Aviation Regulations 14 CFR 43.7 may do 
this action. Make an entry in the aircraft records showing 
compliance with this portion of the AD following 14 CFR 43.9.
    (2) For MSN 545 and MSN 1001 through MSN 1180, within 180 days 
after the effective date of this AD:
    (i) Update the air data, attitude, and heading reference system 
(ADAHRS) software following the accomplishment instructions of 
Honeywell International Inc. Service Bulletin KSG 7200-34-09, 
Revision 0, dated September 24, 2009; or
    (ii) Replace ADAHRS unit KSG 7200 Honeywell Part Number (P/N) 
065-00188-5102, Software Version MOD 02/02 (Pilatus P/N 
985.99.12.192) with a new ADAHRS unit with Honeywell P/N 065-00188-
5103 (Pilatus P/N 985.99.12.205) following the accomplishment 
instructions of PILATUS AIRCRAFT LTD. PILATUS PC-12 Service Bulletin 
No: 34-022, dated October 5, 2009.
    (3) For MSN 545 and 1001 through 1180, before further flight 
after the actions required by paragraph (f)(2) of this AD, remove 
PILATUS AIRCRAFT LTD. Temporary Revision No. 11 to PC-12/47E Pilot's 
Operating Handbook, Report No. 02277, dated March 18, 2009.
    (4) Do not install an ADAHRS unit with Honeywell P/N 065-00188-
5102 (Pilatus P/N 985.99.12.192) on any affected Model PC-12/47E 
airplane, as follows:
    (i) For MSN 545 and 1001 through 1180 airplanes, as of 180 days 
after the effective date of this AD; and
    (ii) For all other MSNs, as of the effective date of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office,

[[Page 65496]]

FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane 
Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; 
telephone: (816) 329-4059; fax: (816) 329-4090. Before using any 
approved AMOC on any airplane to which the AMOC applies, notify your 
appropriate principal inspector (PI) in the FAA Flight Standards 
District Office (FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2009-0249, dated November 20, 2009, PILATUS AIRCRAFT LTD. Temporary 
Revision No. 11 to PC-12/47E Pilot's Operating Handbook, Report No. 
02277, dated March 18, 2009; Honeywell International Inc. Service 
Bulletin KSG 7200-34-09, Revision 0, dated September 24, 2009; and 
PILATUS AIRCRAFT LTD. PILATUS PC-12 Service Bulletin No: 34-022, 
dated October 5, 2009, for related information.

    Issued in Kansas City, Missouri, on December 4, 2009.
William Timberlake,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-29457 Filed 12-9-09; 8:45 am]
BILLING CODE 4910-13-P