Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes, 20919-20922 [E6-6055]

Download as PDF Federal Register / Vol. 71, No. 78 / Monday, April 24, 2006 / Proposed Rules 20919 Actions Compliance Procedures (2) If any signs of cracks, corrosion, or fractures are found on any wing attach barrel nut during the inspection required in paragraph (e)(1) of this AD, replace that wing attach barrel nut, bolt, and retainer with new parts and install to the correct torque value. (3) If no signs of cracks, corrosion, or fractures are found during the inspection required in paragraph (e)(1) of this AD, you may reuse the wing attach barrel nuts and bolts if they have been inspected and are free of deformation and irregularities in the threads and meet the minimum breakaway torque requirement. Reinstall inspected parts to the correct torque value. If the wing attach barrel nuts and bolts are not free of deformation and irregularities in the threads or do not meet the minimum breakaway torque requirement, install new parts to the correct torque value. Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. Follow Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, dated March 10, 2006, as applicable, and the appropriate maintenance manual. Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. Follow Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, dated March 10, 2006, as applicable, and the appropriate maintenance manual. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (f) The Manager, Fort Worth Airplane Certification Office, FAA, ATTN: Andrew McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO–43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308–3365; facsimile: (210) 308–3370, has the authority to approve alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. Federal Aviation Administration Related Information (g) Mitsubishi Heavy Industries, Ltd. MU– 2 Service Bulletins JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57– 004A, dated March 10, 2006, pertain to the subject of this AD. To get copies of the documents referenced in this AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 95001; telephone: (972) 934–5480; fax: (972) 934–5488, or Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) 248–3108; facsimile: (972) 248–3321. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at https://dms.dot.gov. The docket number is Docket No. FAA–2006–23578; Directorate Identifier 2006–CE–01–AD. Issued in Kansas City, Missouri, on April 18, 2006. William J. Timberlake, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–6054 Filed 4–21–06; 8:45 am] cchase on PROD1PC60 with PROPOSALS BILLING CODE 4910–13–P VerDate Aug<31>2005 16:27 Apr 21, 2006 Jkt 208001 14 CFR Part 39 [Docket No. FAA–2006–24094; Directorate Identifier 2006–CE–20–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC– 6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1–H2 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to revise Airworthiness Directive (AD) 68–17–03, which applies to all Pilatus Aircraft Ltd. PC–6 series airplanes. AD 68–17–03 currently requires you to repetitively inspect the rudder end rib for cracks and replace the rudder end rib with a modified rudder end rib when you find cracks. Installing the modified rudder end rib terminates the repetitive inspection requirements of AD 68–17– 03. Under a licensing agreement with Pilatus, Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation) produced Model PC–6 series airplanes (manufacturer serial numbers 2001 through 2092) in the United States. AD 68–17–03 was intended to apply to all affected serial numbers of Model PC–6 series airplanes listed on Type Certificate Data Sheet (TCDS) No. 7A15, including the Fairchild-produced airplanes. Consequently, this proposed AD would PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 clarify that all models of the PC–6 airplane on TCDS No. 7A15 (including those models produced under the licensing agreement by Fairchild Republic Company) are included in the applicability. We are proposing this AD to detect and correct cracks in the rudder end rib, which could result in failure of the rudder end rib. This failure could result in loss of directional control. DATES: We must receive comments on this proposed AD by May 24, 2006. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. SUPPLEMENTARY INFORMATION: E:\FR\FM\24APP1.SGM 24APP1 20920 Federal Register / Vol. 71, No. 78 / Monday, April 24, 2006 / Proposed Rules Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2006–24094; Directorate Identifier 2006–CE–20–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, 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 https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion Fatigue cracks found in the bottom nose rib on the rudders of certain Model PC–6 series airplanes prompted us to issue AD 68–17–03, Amendment 39– 634. AD 68–17–03 currently requires the following on all Pilatus Aircraft Ltd. (Pilatus) Model PC–6 series airplanes: • Repetitively inspecting the rudder end rib for cracks; • Replacing the rudder end rib with a modified rudder end rib when you find cracks; and • Terminating the repetitive inspections when the modified rudder end rib is installed. The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, notified the FAA of the need to revise AD 68–17–03 to address an unsafe condition that may exist or could develop on all Pilatus Model PC–6 series airplanes. The FOCA reports that clarification is needed to assure the applicability of AD 68–17–03 to all Model PC–6 series airplanes listed on Type Certificate Data Sheet (TCDS) No. 7A15, including those produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). This condition, if not detected and corrected, could result in failure of the rudder end rib. This failure could result in loss of directional control. Foreign Airworthiness Authority Information The FOCA recently issued Swiss AD Number HB 2005–289, effective date August 23, 2005, to ensure the continued airworthiness of all Model PC–6 series airplanes listed on TC No. 7A15, including those produced in the United States under a licensing agreement with Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). The State of Design for Pilatus Model PC–6 series airplanes is Switzerland and the airplanes are type-certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the FOCA has kept us informed of the situation described above. FAA’s Determination and Requirements of This Proposed AD We are proposing this AD because we have examined the FOCA’s findings, evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design that are certificated for operation in the United States. This proposed AD would revise AD 68–17–03 with a new AD that would retain all actions currently required by AD 68–17–03 and would clarify the applicability of the affected airplanes by: • Identifying those airplanes produced in the United States through a licensing agreement with the Fairchild Republic Company; and • Listing all Pilatus Model PC–6 series airplanes on TCDS No. 7A15 in the applicability section. Costs of Compliance We estimate that this proposed AD would affect 49 airplanes in the U.S. registry. We estimate the following costs to do the proposed inspection: Labor cost Parts cost Total cost per airplane 1 work hour × $80 per hour = $80 .......................................... Not applicable ......................... $80 We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of Total cost on U.S. operators $80 × 49 = $3,920 determining the number of airplanes that may need this replacement: Labor cost Parts cost Total cost per airplane 9 work hours × $80 per hour = $720 .................................................................................................................. $821 $1,541 cchase on PROD1PC60 with PROPOSALS 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, VerDate Aug<31>2005 16:27 Apr 21, 2006 Jkt 208001 ‘‘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. PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Regulatory Findings We have 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. E:\FR\FM\24APP1.SGM 24APP1 20921 Federal Register / Vol. 71, No. 78 / Monday, April 24, 2006 / Proposed Rules For the reasons discussed above, I certify that the 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. Examining the AD Docket Where Can I Go To View the Docket Information? You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at https://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 68–17–03, Amendment 39–634, and adding the following new AD: Pilatus Aircraft LTD: Docket No. FAA–2006– 24094; Directorate Identifier 2006–CE– 20–AD. Comments Due Date (a) We must receive comments on this proposed airworthiness directive (AD) action by May 24, 2006. Affected ADs (b) This AD revises AD 68–17–03, Amendment 39–634. Applicability (c) This AD affects the following airplane models, all manufacturer serial numbers (MSN), that are certificated in any category. Note: MSNs 2001 through 2092 were manufactured by Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, and Fairchild-Hiller Corporation) in the United States under a license agreement and are covered by Type Certificate Data Sheet No. 7A15. (1) PC–6 (2) PC–6–H1 (3) PC–6–H2 (4) PC–6/350 (5) PC–6/350–H1 (6) PC–6/350–H2 (7) PC–6/A (8) PC–6/A–H1 (9) PC–6/A–H2 (10) PC–6/B–H2 (11) PC–6/B1–H2 (12) PC–6/B2–H2 (13) PC–6/B2–H4 (14) PC–6/C–H2 (15) PC–6/C1–H2 Unsafe Condition (d) This AD results from fatigue cracks found in the bottom nose rib on the rudders of certain PC–6 airplanes. We are issuing this AD to detect and correct cracks in the rudder end rib, which could result in failure of the rudder. This failure could lead to loss of rudder control. Compliance (e) To address this problem, you must do the following: Compliance Procedures (1) With the aid of a mirror, inspect the rudder end rib, part number (P/N) 6302.27 (or FAA-approved equivalent P/N) for crack(s). cchase on PROD1PC60 with PROPOSALS Actions Within the next 50 hours time-in-service (TIS) after August 19, 1968 (the effective date of AD 68–17–03). Repetitively inspect thereafter at intervals not to exceed 50 hours TIS. Before further flight after any inspection required in paragraph (e)(1) of this AD in which you find cracks. Installing the modified rudder end rib terminates the repetitive inspection requirement in paragraph (e)(1) of this AD. Follow Pilatus Service Bulletin No. 80, dated April 1968. Not applicable ................................................................. Not applicable. Not applicable ................................................................. Not applicable. (2) If you detect crack(s) during any inspection required in paragraph (e)(1) of this AD, replace the rudder end rib with a modified rudder end rib assembly, P/N 6302.26 Pos. 2, channel reinforcement, P/N 113.40.06.002, and torque tube, P/N 113/40.06.003 (or FAA-approved equivalent P/Ns). (3) 14 CFR 21.303 allows for replacement parts through parts manufacturer approval (PMA). The phrase ‘‘or FAA-approved equivalent part number’’ in this AD is intended to signify those parts that are PMA parts approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD. (4) Installing the modified rudder end rib assembly terminates the repetitive inspection requirement in paragraph (e)(1) of this AD. VerDate Aug<31>2005 16:27 Apr 21, 2006 Jkt 208001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 E:\FR\FM\24APP1.SGM 24APP1 Follow Pilatus Service Bulletin No. 80, dated April 1968. 20922 Federal Register / Vol. 71, No. 78 / Monday, April 24, 2006 / Proposed Rules Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Office, Attn: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; facsimile: (816) 329–4090, has the authority to approve alternative methods of compliance (AMOCs) for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 68–17–03 are approved for this AD. Related Information (h) Swiss AD Number HB 2005–289, effective date August 23, 2005, also addresses the subject of this AD. To get copies of the documents referenced in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at https:// dms.dot.gov. The docket number is Docket No. FAA–2006–24094; Directorate Identifier 2006–CE–20–AD. Issued in Kansas City, Missouri, on April 17, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–6055 Filed 4–21–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY DEPARTMENT OF THE TREASURY For information concerning user fee policy and rates, contact Mr. Jerry Petty, Director, Cost Management Division, 1300 Pennsylvania Avenue, NW., Room 4.5A, Washington, DC 20229. Telephone: (202) 344–1317. FOR FURTHER INFORMATION CONTACT: Bureau of Customs and Border Protection 19 CFR Parts 24 and 111 RIN 1505–AB62 [USCBP–2006–0035] SUPPLEMENTARY INFORMATION: Fees for Certain Services Customs and Border Protection, Homeland Security; Treasury. ACTION: Proposed rule. cchase on PROD1PC60 with PROPOSALS AGENCY: SUMMARY: This document proposes to amend the rules dealing with customs financial and accounting procedures by revising the fees charged for certain customs inspectional services under section 13031 of the Consolidated Omnibus Budget Reconciliation Act of 1985, as amended. These revisions propose to exercise authority provided under recent changes in the pertinent statutory provisions. DATES: Written comments must be received by May 24, 2006. VerDate Aug<31>2005 16:27 Apr 21, 2006 You may submit comments, identified by docket number, by one of the following methods: • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments via docket number USCBP–2006–0035. • Mail: Trade and Commercial Regulations Branch, Office of Regulations and Rulings, Bureau of Customs and Border Protection, 1300 Pennsylvania Avenue, NW. (Mint Annex), Washington, DC 20229. Instructions: All submissions received must include the agency name and docket number for this rulemaking. All comments received will be posted without change to https:// www.regulations.gov, including any personal information provided. For detailed instructions on submitting comments and additional information on the rulemaking process, see the ‘‘Public Participation’’ heading of the SUPPLEMENTARY INFORMATION section of this document. Docket: For access to the docket to read background documents or comments received, go to https:// www.regulations.gov. Submitted comments may also be inspected during the regular business days between the hours of 9 a.m. and 4:30 p.m. at the Office of Regulations and Rulings, Bureau of Customs and Border Protection, 799 9th Street, NW., 5th Floor, Washington, DC. Arrangements to inspect submitted comments should be made in advance by calling Mr. Joseph Clark at (202) 572–8768. ADDRESSES: Jkt 208001 Public Participation Interested persons are invited to participate in this rule-making by submitting written data, views, or arguments on all aspects of the proposed rule. The Bureau of Customs and Border Protection (CBP) also invites comments that relate to the economic, environmental, or federalism effects that might result from this proposed rule. If appropriate to a specific comment, the commenter should reference the specific portion of the proposed rule, explain the reason for any recommended change, and include data, information, or authority that support such recommended change. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 Background CBP collects fees to pay for the costs incurred in providing customs services in connection with certain activities under the authority of section 13031 of the Consolidated Omnibus Budget Reconciliation Act of 1985 (COBRA), as amended, codified at section 19 U.S.C. 58c. On October 22, 2004, the President signed the American Jobs Creation Act of 2004 (Pub. L. 108–357). Section 892 of the American Jobs Creation Act amended 19 U.S.C. 58c to renew the fees provided under COBRA, which would have otherwise expired March 1, 2005, and to allow the Secretary of the Treasury to increase such fees by an amount not to exceed 10 percent in the period beginning fiscal year 2006 through the period for which fees are authorized by law. It is noted that the law specifically mentions the Secretary of the Treasury, even though CBP is now a component of the Department of Homeland Security. Regulations concerning user fees, among other customs revenue functions, were retained by the Secretary of the Treasury pursuant to Treasury Department Order No. 100–16. In accordance with the current statutory provisions, CBP is proposing to amend the regulations by increasing the fees for customs services provided in connection with (1) the arrival of certain commercial vessels, commercial trucks, railroad cars, private aircraft and private vessels, passengers aboard commercial aircraft and commercial vessels, and barges or other bulk carrier arrivals, (2) each item of dutiable mail for which a customs officer prepares documentation, and (3) annual customs brokers permits. CBP is proposing to increase the fees by the amounts authorized so that they more accurately reflect the actual costs of providing the services for which they are charged. None of the user fees being raised in this package have been adjusted since their implementation in 1986. However, the costs incurred by CBP in performing certain customs inspection services have continued to grow because of higher volumes, greater varieties of cargo and increased security concerns which require inspections of individuals and conveyances entering the United States. As a result, CBP currently collects COBRA fees covering only thirty-two percent of the costs incurred by the agency. With this proposed increase, we estimate COBRA fees will generate an additional $26 million annually. Approximately 84 percent of these fees come from individual travelers, which are E:\FR\FM\24APP1.SGM 24APP1

Agencies

[Federal Register Volume 71, Number 78 (Monday, April 24, 2006)]
[Proposed Rules]
[Pages 20919-20922]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-6055]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24094; Directorate Identifier 2006-CE-20-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC-
6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, 
PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, 
and PC-6/C1-H2 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to revise Airworthiness Directive (AD) 68-17-03, 
which applies to all Pilatus Aircraft Ltd. PC-6 series airplanes. AD 
68-17-03 currently requires you to repetitively inspect the rudder end 
rib for cracks and replace the rudder end rib with a modified rudder 
end rib when you find cracks. Installing the modified rudder end rib 
terminates the repetitive inspection requirements of AD 68-17-03. Under 
a licensing agreement with Pilatus, Fairchild Republic Company (also 
identified as Fairchild Industries, Fairchild Heli Porter, or 
Fairchild-Hiller Corporation) produced Model PC-6 series airplanes 
(manufacturer serial numbers 2001 through 2092) in the United States. 
AD 68-17-03 was intended to apply to all affected serial numbers of 
Model PC-6 series airplanes listed on Type Certificate Data Sheet 
(TCDS) No. 7A15, including the Fairchild-produced airplanes. 
Consequently, this proposed AD would clarify that all models of the PC-
6 airplane on TCDS No. 7A15 (including those models produced under the 
licensing agreement by Fairchild Republic Company) are included in the 
applicability. We are proposing this AD to detect and correct cracks in 
the rudder end rib, which could result in failure of the rudder end 
rib. This failure could result in loss of directional control.

DATES: We must receive comments on this proposed AD by May 24, 2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

[[Page 20920]]

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-24094; Directorate Identifier 2006-CE-20-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, 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 https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    Fatigue cracks found in the bottom nose rib on the rudders of 
certain Model PC-6 series airplanes prompted us to issue AD 68-17-03, 
Amendment 39-634. AD 68-17-03 currently requires the following on all 
Pilatus Aircraft Ltd. (Pilatus) Model PC-6 series airplanes:
     Repetitively inspecting the rudder end rib for cracks;
     Replacing the rudder end rib with a modified rudder end 
rib when you find cracks; and
     Terminating the repetitive inspections when the modified 
rudder end rib is installed.
    The Federal Office for Civil Aviation (FOCA), which is the 
airworthiness authority for Switzerland, notified the FAA of the need 
to revise AD 68-17-03 to address an unsafe condition that may exist or 
could develop on all Pilatus Model PC-6 series airplanes. The FOCA 
reports that clarification is needed to assure the applicability of AD 
68-17-03 to all Model PC-6 series airplanes listed on Type Certificate 
Data Sheet (TCDS) No. 7A15, including those produced in the United 
States through a licensing agreement between Pilatus and Fairchild 
Republic Company (also identified as Fairchild Industries, Fairchild 
Heli Porter, or Fairchild-Hiller Corporation).
    This condition, if not detected and corrected, could result in 
failure of the rudder end rib. This failure could result in loss of 
directional control.

Foreign Airworthiness Authority Information

    The FOCA recently issued Swiss AD Number HB 2005-289, effective 
date August 23, 2005, to ensure the continued airworthiness of all 
Model PC-6 series airplanes listed on TC No. 7A15, including those 
produced in the United States under a licensing agreement with Pilatus 
and Fairchild Republic Company (also identified as Fairchild 
Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation).
    The State of Design for Pilatus Model PC-6 series airplanes is 
Switzerland and the airplanes are type-certificated for operation in 
the United States under the provisions of section 21.29 of the Federal 
Aviation Regulations (14 CFR 21.29) and the applicable bilateral 
airworthiness agreement.
    Under this bilateral airworthiness agreement, the FOCA has kept us 
informed of the situation described above.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we have examined the FOCA's 
findings, evaluated all information and determined the unsafe condition 
described previously is likely to exist or develop on other products of 
the same type design that are certificated for operation in the United 
States.
    This proposed AD would revise AD 68-17-03 with a new AD that would 
retain all actions currently required by AD 68-17-03 and would clarify 
the applicability of the affected airplanes by:
     Identifying those airplanes produced in the United States 
through a licensing agreement with the Fairchild Republic Company; and
     Listing all Pilatus Model PC-6 series airplanes on TCDS 
No. 7A15 in the applicability section.

Costs of Compliance

    We estimate that this proposed AD would affect 49 airplanes in the 
U.S. registry.
    We estimate the following costs to do the proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                        Total cost  per
           Labor cost                  Parts cost           airplane           Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $80 per hour = $80  Not applicable.....               $80   $80 x 49 = $3,920
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of airplanes that may need 
this replacement:

------------------------------------------------------------------------
                                                        Total cost  per
             Labor cost                  Parts cost         airplane
------------------------------------------------------------------------
9 work hours x $80 per hour = $720..            $821             $1,541
------------------------------------------------------------------------

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 have 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.

[[Page 20921]]

    For the reasons discussed above, I certify that the 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.

Examining the AD Docket

Where Can I Go To View the Docket Information?

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at https://dms.dot.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5227) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 Airworthiness Directive 
(AD) 68-17-03, Amendment 39-634, and adding the following new AD:

Pilatus Aircraft LTD: Docket No. FAA-2006-24094; Directorate 
Identifier 2006-CE-20-AD.

Comments Due Date

    (a) We must receive comments on this proposed airworthiness 
directive (AD) action by May 24, 2006.

Affected ADs

    (b) This AD revises AD 68-17-03, Amendment 39-634.

Applicability

    (c) This AD affects the following airplane models, all 
manufacturer serial numbers (MSN), that are certificated in any 
category.

    Note: MSNs 2001 through 2092 were manufactured by Fairchild 
Republic Company (also identified as Fairchild Industries, Fairchild 
Heli Porter, and Fairchild-Hiller Corporation) in the United States 
under a license agreement and are covered by Type Certificate Data 
Sheet No. 7A15.

    (1) PC-6
    (2) PC-6-H1
    (3) PC-6-H2
    (4) PC-6/350
    (5) PC-6/350-H1
    (6) PC-6/350-H2
    (7) PC-6/A
    (8) PC-6/A-H1
    (9) PC-6/A-H2
    (10) PC-6/B-H2
    (11) PC-6/B1-H2
    (12) PC-6/B2-H2
    (13) PC-6/B2-H4
    (14) PC-6/C-H2
    (15) PC-6/C1-H2

Unsafe Condition

    (d) This AD results from fatigue cracks found in the bottom nose 
rib on the rudders of certain PC-6 airplanes. We are issuing this AD 
to detect and correct cracks in the rudder end rib, which could 
result in failure of the rudder. This failure could lead to loss of 
rudder control.

Compliance

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
            Actions                   Compliance           Procedures
------------------------------------------------------------------------
(1) With the aid of a mirror,   Within the next 50      Follow Pilatus
 inspect the rudder end rib,     hours time-in-service   Service
 part number (P/N) 6302.27 (or   (TIS) after August      Bulletin No.
 FAA-approved equivalent P/N)    19, 1968 (the           80, dated April
 for crack(s).                   effective date of AD    1968.
                                 68-17-03).
                                 Repetitively inspect
                                 thereafter at
                                 intervals not to
                                 exceed 50 hours TIS.
(2) If you detect crack(s)      Before further flight   Follow Pilatus
 during any inspection           after any inspection    Service
 required in paragraph (e)(1)    required in paragraph   Bulletin No.
 of this AD, replace the         (e)(1) of this AD in    80, dated April
 rudder end rib with a           which you find          1968.
 modified rudder end rib         cracks. Installing
 assembly, P/N 6302.26 Pos. 2,   the modified rudder
 channel reinforcement, P/N      end rib terminates
 113.40.06.002, and torque       the repetitive
 tube, P/N 113/40.06.003 (or     inspection
 FAA-approved equivalent P/Ns).  requirement in
                                 paragraph (e)(1) of
                                 this AD.
(3) 14 CFR 21.303 allows for    Not applicable........  Not applicable.
 replacement parts through
 parts manufacturer approval
 (PMA). The phrase ``or FAA-
 approved equivalent part
 number'' in this AD is
 intended to signify those
 parts that are PMA parts
 approved through identicality
 to the design of the part
 under the type certificate
 and replacement parts to
 correct the unsafe condition
 under PMA (other than
 identicality). If parts are
 installed that are identical
 to the unsafe parts, then the
 corrective actions of the AD
 affect these parts also. In
 addition, equivalent
 replacement parts to correct
 the unsafe condition under
 PMA (other than identicality)
 may also be installed
 provided they meet current
 airworthiness standards,
 which include those actions
 cited in this AD.
(4) Installing the modified     Not applicable........  Not applicable.
 rudder end rib assembly
 terminates the repetitive
 inspection requirement in
 paragraph (e)(1) of this AD.
------------------------------------------------------------------------


[[Page 20922]]

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Standards Office, Attn: Doug Rudolph, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090, has the authority to approve alternative methods of 
compliance (AMOCs) for this AD, if requested using the procedures 
found in 14 CFR 39.19.
    (g) AMOCs approved for AD 68-17-03 are approved for this AD.

Related Information

    (h) Swiss AD Number HB 2005-289, effective date August 23, 2005, 
also addresses the subject of this AD. To get copies of the 
documents referenced in this AD, contact Pilatus Aircraft Ltd., 
Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 
41 619 63 19; facsimile: +41 41 619 6224. To view the AD docket, go 
to the Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC, or on the Internet at https://dms.dot.gov. The 
docket number is Docket No. FAA-2006-24094; Directorate Identifier 
2006-CE-20-AD.

    Issued in Kansas City, Missouri, on April 17, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-6055 Filed 4-21-06; 8:45 am]
BILLING CODE 4910-13-P
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