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, 47716-47720 [05-16000]

Download as PDF 47716 Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations section 1344 (Passenger Carrier Use), and section 1349(b), (Adverse Personnel Actions); (iv) The Federal Tort Claims Act and any other Federal tort liability statute; (v) The Ethics in Government Act of 1978; (vi) Internal Revenue Code of 1986, section 1043 (Sale of Property to Comply with Conflict-of-Interest Requirements); and (vii) Title 41, United States Code, section 423 (Prohibition on Former Official’s Acceptance of Compensation From Contractor). (2) Does not have any right or expectation for Federal employment solely on the basis of his or her detail; (3) May not have access to any trade secrets or to any other nonpublic information which is of commercial value to the private sector organization from which he or she is detailed; (4) Is subject to such regulations as the President may prescribe; and (5) Is covered by 5 U.S.C. chapter 81, Compensation for Work Injuries, as provided in 5 U.S.C. 3704(c). (c) Individuals detailed under this part may be supervised either by Federal or private sector managers. For example, a Federal employee on detail to a private sector organization may be supervised by a private sector manager. Likewise, a private sector employee on detail to an agency may be supervised by a Federal manager. (d) As provided in 5 U.S.C. 3704(d), a private sector organization may not charge the Federal Government, as direct or indirect costs under a Federal contract, for the costs of pay or benefits paid by that private sector organization to an employee detailed to an agency under this part. (e) Details may be terminated by the agency (agency head or designee) or private sector organization concerned for any reason at any time. § 370.107 Details to small business concerns. (a) The head of each agency must take such actions as may be necessary to ensure that, of the details made to private sector organizations in each calendar year, at least 20 percent are to small business concerns, in accordance with 5 U.S.C. 3703(e)(1). (b) Agencies must round up to the nearest whole number when calculating the percentage of details to small business concerns needed to meet the requirements of this section. For example, if an agency detailed 11 individuals to private sector organizations during a given year, to meet the 20 percent requirement, that agency must have made at least 3 VerDate jul<14>2003 13:13 Aug 12, 2005 Jkt 205001 (rounded up from 2.2) of these details to small business concerns. (c) For purposes of this section, ‘‘year’’ refers to the 12-month period beginning on date of the enactment of the Act, December 17, 2002, and each succeeding 12-month period in which any assignments are made. Assignments ‘‘made’’ in a year are those commencing in such year, in accordance with 5 U.S.C. 3703(e)(2). (d) Agencies that do not meet the requirements of this section are subject to the reporting requirements in 5 U.S.C. 3703(e)(3). (e) An agency that makes fewer than five details to private sector organizations in any year is not subject to this section. § 370.108 Reporting requirements. (a) Agencies using this part must prepare and submit to OPM semiannual reports in accordance with 5 U.S.C. 3706 which must include: (1) The total number of individuals detailed to, and the total number of individuals detailed from, the agency during the report period; (2) A brief description of each detail reported under paragraph (a)(1) of this section including: (i) The name of the detailed individual, and the private sector organization and the agency (including the specific bureau or other agency component) to or from which such individual was detailed; (ii) The respective positions to and from which the individual was detailed, including the duties and responsibilities and the pay grade or level associated with each; and (iii) The duration and objectives of the individual’s detail; and (3) Such other information as OPM considers appropriate. (b) Reports are due to OPM no later than April 7 and October 7 of each year for the immediately preceding 6-month periods ending March 31 and September 30, respectively. (c) Agencies that do not meet the requirements of § 370.107 must prepare and submit annual reports to Congress in accordance with 5 U.S.C. 3703(e)(3), as appropriate. § 370.109 Agency plans. Before detailing agency employees or receiving private sector employees under this part, an agency must establish an Information Technology Exchange Program Plan. The plan must include, but is not limited to, the following elements: (a) Designation of the agency officials with authority to review and approve details; PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (b) Estimated number of candidates needed, both private sector and Federal employees, to address IT workforce needs within the agency; (c) Criteria for the selection of agency employees for a detail under this part. At a minimum, each agency must: (1) Announce the detail, including eligibility requirements, to all eligible employees; (2) Provide for employee nomination by their organization or self-nomination, to include endorsement by their respective supervisor; (3) Forward nominations to designated agency reviewing and approving official for final selection. (4) Consider: (i) The extent to which the employee’s current competencies and skills are being utilized in the agency; (ii) The employee’s capability to improve, enhance, or learn skills and acquire competencies needed in the agency; and (iii) The benefits to the agency which would result from selecting the employee for detail. (d) Return rights and continuing service requirements for Federal employees returning from a detail; and (e) Documentation and recordkeeping requirements sufficient to allow reconstruction of each action taken under this part to meet agency reporting requirements under § 370.108(a) and (b). [FR Doc. 05–16092 Filed 8–12–05; 8:45 am] BILLING CODE 6325–39–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20515; Directorate Identifier 2005–CE–09–AD; Amendment 39– 14221; AD 2005–17–01] 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), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic Company and Fairchild Heli Porter) Model PC–6 airplanes. This AD requires E:\FR\FM\15AUR1.SGM 15AUR1 Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations you to repetitively inspect the stabilizertrim attachment and structural components for cracks, corrosion, and discrepancies and replace any defective part with a new part. This AD also requires you to replace all Fairchild connecting pieces, part number (P/N) 6232.0026.XX, with a Pilatus connecting piece and requires you to replace fittings without an index after the P/N with an improved part. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct defective stabilizertrim attachments and surrounding structural components, which could result in failure of the stabilizer-trim attachment. This failure could lead to loss of control of the airplane. DATES: This AD becomes effective on September 29, 2005. As of September 29, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576. 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 20590– 001 or on the Internet at http:// dms.dot.gov. The docket number is FAA–2005–20515; Directorate Identifier 2005–CE–09–AD. 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: Discussion What events have caused this AD? The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, recently notified FAA that an unsafe condition may exist on all Pilatus Model PC–6 airplanes. The FOCA reports that the lower attachment bracket of the horizontal stabilizer actuator broke, which resulted in an emergency landing outside the airport. The FOCA also reports two other instances of total failure of the stabilizer trim attachment on in-service airplanes. What is the potential impact if FAA took no action? If not detected and VerDate jul<14>2003 13:13 Aug 12, 2005 Jkt 205001 corrected, defects in the stabilizer-trim attachment and surrounding structural components could cause the stabilizertrim attachment to fail. This failure could lead to loss of control of the airplane. Has FAA taken any action to this point? We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Pilatus Model PC–6 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on March 24, 2005 (70 FR 15019). The NPRM proposed to require you to: —Inspect the stabilizer-trim attachment and structural components (the fitting, the connecting piece, the bearing fork, the bearing support assembly, and the auxiliary frame, as applicable) for cracks and corrosion; —Inspect the diameters of the boltholes on the fittings, auxiliary frame, and connecting piece (as applicable) for discrepancies; —Replace any cracked, corroded, or defective part with a new part; and —Replace all Fairchild connecting pieces with a Pilatus connecting piece. We received comments on the NPRM requesting the following: —Incorporate revised service to include a procedure for replacing certain fittings with an improved part and to correct the allowable limits of the actuator attachment hole diameters; —Change the repetitive inspection intervals; and —Clarify the applicability of the affected airplanes. As a result of the above comments, we issued a supplemental NPRM that was published in the Federal Register on June 14, 2005 (34401). The Supplemental NPRM proposed to require you to: —Inspect the stabilizer-trim attachment and structural components (the fitting, the connecting piece, the bearing fork, the bearing support assembly, and the auxiliary frame, as applicable) for cracks and corrosion; —Inspect the diameters of the boltholes on the fittings, auxiliary frame, and connecting piece (as applicable) for discrepancies; —Replace any cracked part with a new part; —Repair or replace corroded or defective part; —Replace all Fairchild connecting pieces, P/N 6232.0026.XX with a Pilatus connecting piece. The Fairchild part has a rivet in the PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 47717 middle that is not on the Pilatus part; and —Replace all fittings, P/N 116.40.06.033 without an index after the P/N with an improved part, P/N 116.40.06.033 with an index after the P/N or P/N 116.40.06.112. Comments Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. Pilatus Aircraft Ltd. submitted a comment stating that they have no further comments on the Supplemental NPRM. Comment Issue: Update Reference to the Swiss AD What is the commenter’s concern? FOCA has superseded Swiss AD HB– 2005–080, effective date March 2, 2005, with Swiss AD HB–2005–263, effective date June 16, 2005. The commenter requests that the reference to the Swiss AD be changed to incorporate the new AD number. What is FAA’s response to the concern? We concur with the commenter and will change the final rule AD action. What is FAA’s final determination on this issue? We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for the changes discussed above and minor editorial corrections. We have determined that these changes and minor corrections: —Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and —Do not add any additional burden upon the public than was already proposed in the NPRM. Docket Information Where can I go to view the docket information? You may view the AD docket that contains information relating to this subject in person at the DMS Docket Offices between 9 a.m. and 5 p.m. (eastern standard time), Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800– 647–5227) is located on the plaza level of the Department of Transportation NASSIF Building at the street address stated in ADDRESSES. You may also view the AD docket on the Internet at http://dms.dot.gov. Changes to 14 CFR Part 39—Effect on the AD How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), E:\FR\FM\15AUR1.SGM 15AUR1 47718 Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations which governs the FAA’s AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Labor cost Parts cost 11 work hours × $65 per hour = $715 ............ Not applicable ................................................. We estimate the following costs to do any necessary replacements that will be Costs of Compliance How many airplanes does this AD impact? We estimate that this AD affects 41 airplanes in the U.S. registry. What is the cost impact of this AD on owners/operators of the affected airplanes? We estimate the following costs to do the inspections: Total cost per airplane required based on the results of the inspections. We have no way of $715 Total cost per airplane to replace all parts Parts cost 10 work hours × $65 = $650 ............................................ $2,000 to replace all parts ............................................... What authority does FAA have for issuing this rulemaking action? 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 AD. Regulatory Findings Will this AD impact various entities? We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Will this AD involve a significant rule or regulatory action? 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 the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and VerDate jul<14>2003 13:13 Aug 12, 2005 Jkt 205001 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 summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2005–20515; Directorate Identifier 2005–CE–09–AD’’ in your request. $715 × 41 = $29,315 determining the number of airplanes that may need these replacements: Labor cost Authority for This Rulemaking Total cost on U.S. operators $650 + $2,000 = $2,650 What Other ADs Are Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplanes, all manufacturer serial numbers (MSN), that are certificated in any category. Note 1: These airplanes are also identified as Fairchild Republic Company PC–6 series airplanes and Fairchild Heli Porter PC–6 series airplanes. Models PART 39—AIRWORTHINESS DIRECTIVES (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 1. The authority citation for part 39 continues to read as follows: What Is the Unsafe Condition Presented in This AD? 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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. FAA amends § 39.13 by adding a new AD to read as follows: I 2005–17–01 Pilatus Aircraft Ltd.: Amendment 39–14221; Docket No. FAA–2005–20515; Directorate Identifier 2005–CE–09–AD. When Does This AD Become Effective? (a) This AD becomes effective on September 29, 2005. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct cracks in the stabilizer-trim attachment and surrounding structural components, which could result in failure of the stabilizer-trim attachment. This failure could lead to loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: E:\FR\FM\15AUR1.SGM 15AUR1 Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations Actions Compliance (1) Inspect the following: (i) the stabilizer-trim attachment and structural components (fitting, connecting piece, bearing fork, bearing support assembly, and auxiliary frame, as applicable) for cracks and corrosion; and. (ii) the diameters of the actuator attachment bolt holes on the fittings, auxiliary frame, and connecting piece (as applicable) for discrepancies. (2) If cracks are found during any inspection required in paragraph (e)(1)(i) of this AD, replace the defective part with a new part. (3) If corrosion or discrepancies are found during any inspection required in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD, do the following: (i) replace the defective part with a new part if the corrosion or discrepancy is beyond the repairable limits stated in the service information; or. (ii) repair the defective part if the corrosion or discrepancy is within the repairable limits stated in the service information. (4) Replace the following: (i) all Fairchild connecting pieces, part number (P/N) 6232.0026.XX, with a Pilatus connecting piece, P/N 6232.0026.XX. The Fairchild part has a rivet in the middle that is not on the Pilatus part; and. (ii) all fittings, P/N 116.40.06.033 without an index after the P/N, with an improved part, P/ N 116.40.06.033 with an index of ‘‘A’’ or ‘‘B’’ after the P/N or with P/N 116.40.06.112. (5) Do not install any of the following: (i) Fairchild connecting piece, P/N 6232.0026.XX (it has a rivet in the middle that is not on the Pilatus part); and. (ii) fitting, P/N 116.40.06.033, without an index after the part number. Procedures Within the next 100 hours time-in-service (TIS) after September 29, 2005 (the effective date of this AD). Repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first. Follow Pilatus PC–6 Service Bulletin No. 53– 001, Rev. No. 1, dated June 1, 2005. Replace the defective part before further flight after the inspection in which cracks are found. After each replacement, continue with the repetitive inspection requirement in paragraph (e)(1) of this AD. Follow Pilatus PC–6 Service Bulletin No. 53– 001, Rev. No. 1, dated June 1, 2005. Replace or repair the defective part before further flight after the inspection in which corrosion or discrepancies are found. After each replacement or repair, continue with the repetitive inspection requirement in paragraph (e)(1) of this AD. Follow Pilatus PC–6 Service Bulletin No. 53– 001, Rev. No. 1, dated June 1, 2005. Within the next 100 hours TIS after September 29, 2005 (the effective date of this AD). After replacement, repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first. If after the inspection required in paragraph (e)(1) of this AD, you determine that you already have a P/N 116.40.06.033 with an index of ‘‘A’’ or ‘‘B’’ or a P/N 116.40.06.112 installed, repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first after the part was installed. Follow Pilatus PC–6 Service Bulletin No. 53– 001, Rev. No. 1, dated June 1, 2005. As of September 29, 2005 (the effective date of this AD). Follow Pilatus PC–6 Service Bulletin No. 53– 001, Rev. No. 1, dated June 1, 2005. Note 2: Even though not required in this AD, the FAA recommends that you send all defective parts to Pilatus at the address specified in paragraph (h) of this AD. With the part, include the aircraft serial number, flying hours, and cycles. Is There Other Information That Relates to This Subject? May I Request an Alternative Method of Compliance? (g) Swiss AD HB–2005–263, effective date June 16, 2005, also addresses the subject of this AD. (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, FAA, Small Airplane VerDate jul<14>2003 14:26 Aug 12, 2005 47719 Jkt 205001 Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Pilatus PC–6 Service Bulletin No. 53–001, Rev. No. 1, dated June 1, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Pilatus Aircraft Ltd., PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http:// www.archives.gov/federal_register/code_ of_federal_regulations/ibr_locations.html or call (202) 741–6030. 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 20590–001 or on the Internet at http://dms.dot.gov. The docket number is FAA–2005–20515; Directorate Identifier 2005–CE–09–AD. E:\FR\FM\15AUR1.SGM 15AUR1 47720 Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations Issued in Kansas City, Missouri, on August 8, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–16000 Filed 8–12–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22073; Directorate Identifier 2005–NM–140–AD; Amendment 39–14219; AD 2005–16–13] RIN 2120–AA64 Airworthiness Directives; Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 airplanes. This AD requires a one-time general visual inspection for any damaged wiring, splice, connector, and pins for the fuel standby feed pumps and replacement of any damaged wiring, splice, connector, or pin. This AD also requires replacement of the power and ground wires for the fuel standby feed pumps. This AD results from reports of evidence of overheating found on the feeder wires of the left and right fuel standby feed pumps. We are issuing this AD to detect and correct damaged wiring for the fuel standby feed pumps, which could result in an ignition source in an area where fuel vapor may be present, and a consequent fire or explosion. DATES: Effective Date: August 30, 2005. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 30, 2005. We must receive comments on this AD by October 14, 2005. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. VerDate jul<14>2003 13:13 Aug 12, 2005 Jkt 205001 • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC 20590. • 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. Contact Gulfstream Aerospace Corporation, P.O. Box 2206, Mail Station D–25, Savannah, Georgia 31402– 2206, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The Civil Aviation Administration of Israel (CAAI), which is the airworthiness authority for Israel, notified us that an unsafe condition may exist on certain Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 airplanes. The CAAI advises that, while troubleshooting a fuel quantity indication condition on a Model Gulfstream 200 airplane, technicians found evidence of overheating on the feeder wires splice of the left fuel standby feed pump 3Q1. Subsequent investigation revealed a similar condition in the wiring of the left and right fuel standby feed pumps of four other Model Gulfstream 200 airplanes. This condition, if not corrected, could result in an ignition source in an area where fuel vapor may be present, and a consequent fire or explosion. The subject fuel standby feed pump wiring on Model Galaxy airplanes is identical to that on the affected Model Gulfstream 200 airplanes. Therefore, both of these models may be subject to the same unsafe condition. Relevant Service Information Gulfstream Aerospace LP has issued Alert Service Bulletin 200–28A–261, dated June 7, 2005. The alert service bulletin describes procedures for performing a visual inspection of the wiring, splice, connector, and pins for the left (3Q1) and right (4Q1) fuel standby feed pumps for damage, and for replacing any damaged wiring, splice, connector, or pin with a new wire, splice, connector, or pin, as applicable. Damage includes evidence of overheating and worn or chafed insulation. The alert service bulletin PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 also describes procedures for replacing the power and ground wires for the fuel standby feed pumps with 12-AmericanWire-Gauge (AWG) wires. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The CAAI mandated the alert service bulletin and issued Israeli airworthiness directive 28–05–06–08, dated July 3, 2005, to ensure the continued airworthiness of these airplanes in Israel. FAA’s Determination and Requirements of This AD These airplane models are manufactured in Israel and 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. Pursuant to this bilateral airworthiness agreement, the CAAI has kept the FAA informed of the situation described above. We have examined the CAAI’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are issuing this AD to detect and correct any damaged wiring, splice, connector, or pin for the fuel standby feed pumps, which could result in an ignition source in an area where fuel vapor may be present, and a consequent fire or explosion. This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the AD and Alert Service Bulletin’’. Clarification of Inspection in the Israeli Airworthiness Directive The Israeli airworthiness directive states only to ‘‘inspect’’ the wiring; it does not define what type of inspection should be done. We have determined that the inspection in the Israeli airworthiness directive should be described as a ‘‘general visual inspection.’’ Note 1 has been included in this AD to define this type of inspection. Differences Between the AD and Alert Service Bulletin The Accomplishment Instructions of Gulfstream Alert Service Bulletin 200– 28A–261, dated June 7, 2005, instruct operators to inspect the wiring for worn or chafed insulation; however, it gives no repair instructions if any worn or chafed insulation is found. This AD requires operators to replace any wiring E:\FR\FM\15AUR1.SGM 15AUR1

Agencies

[Federal Register Volume 70, Number 156 (Monday, August 15, 2005)]
[Rules and Regulations]
[Pages 47716-47720]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16000]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD; 
Amendment 39-14221; AD 2005-17-01]
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), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA adopts a new airworthiness directive (AD) for all 
Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic 
Company and Fairchild Heli Porter) Model PC-6 airplanes. This AD 
requires

[[Page 47717]]

you to repetitively inspect the stabilizer-trim attachment and 
structural components for cracks, corrosion, and discrepancies and 
replace any defective part with a new part. This AD also requires you 
to replace all Fairchild connecting pieces, part number (P/N) 
6232.0026.XX, with a Pilatus connecting piece and requires you to 
replace fittings without an index after the P/N with an improved part. 
This AD results from mandatory continuing airworthiness information 
(MCAI) issued by the airworthiness authority for Switzerland. We are 
issuing this AD to detect and correct defective stabilizer-trim 
attachments and surrounding structural components, which could result 
in failure of the stabilizer-trim attachment. This failure could lead 
to loss of control of the airplane.

DATES: This AD becomes effective on September 29, 2005.
    As of September 29, 2005, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: To get the service information identified in this AD, 
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576.
    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 20590-001 or on the Internet at http://
dms.dot.gov. The docket number is FAA-2005-20515; Directorate 
Identifier 2005-CE-09-AD.

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:

Discussion

    What events have caused this AD? The Federal Office for Civil 
Aviation (FOCA), which is the airworthiness authority for Switzerland, 
recently notified FAA that an unsafe condition may exist on all Pilatus 
Model PC-6 airplanes. The FOCA reports that the lower attachment 
bracket of the horizontal stabilizer actuator broke, which resulted in 
an emergency landing outside the airport.
    The FOCA also reports two other instances of total failure of the 
stabilizer trim attachment on in-service airplanes.
    What is the potential impact if FAA took no action? If not detected 
and corrected, defects in the stabilizer-trim attachment and 
surrounding structural components could cause the stabilizer-trim 
attachment to fail. This failure could lead to loss of control of the 
airplane.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to all Pilatus Model PC-6 airplanes. 
This proposal was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on March 24, 2005 (70 FR 15019). The NPRM 
proposed to require you to:

--Inspect the stabilizer-trim attachment and structural components (the 
fitting, the connecting piece, the bearing fork, the bearing support 
assembly, and the auxiliary frame, as applicable) for cracks and 
corrosion;
--Inspect the diameters of the boltholes on the fittings, auxiliary 
frame, and connecting piece (as applicable) for discrepancies;
--Replace any cracked, corroded, or defective part with a new part; and
--Replace all Fairchild connecting pieces with a Pilatus connecting 
piece.

    We received comments on the NPRM requesting the following:

--Incorporate revised service to include a procedure for replacing 
certain fittings with an improved part and to correct the allowable 
limits of the actuator attachment hole diameters;
--Change the repetitive inspection intervals; and
--Clarify the applicability of the affected airplanes.

    As a result of the above comments, we issued a supplemental NPRM 
that was published in the Federal Register on June 14, 2005 (34401). 
The Supplemental NPRM proposed to require you to:

--Inspect the stabilizer-trim attachment and structural components (the 
fitting, the connecting piece, the bearing fork, the bearing support 
assembly, and the auxiliary frame, as applicable) for cracks and 
corrosion;
--Inspect the diameters of the boltholes on the fittings, auxiliary 
frame, and connecting piece (as applicable) for discrepancies;
--Replace any cracked part with a new part;
--Repair or replace corroded or defective part;
--Replace all Fairchild connecting pieces, P/N 6232.0026.XX with a 
Pilatus connecting piece. The Fairchild part has a rivet in the middle 
that is not on the Pilatus part; and
--Replace all fittings, P/N 116.40.06.033 without an index after the P/
N with an improved part, P/N 116.40.06.033 with an index after the P/N 
or P/N 116.40.06.112.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD.
    Pilatus Aircraft Ltd. submitted a comment stating that they have no 
further comments on the Supplemental NPRM.

Comment Issue: Update Reference to the Swiss AD

    What is the commenter's concern? FOCA has superseded Swiss AD HB-
2005-080, effective date March 2, 2005, with Swiss AD HB-2005-263, 
effective date June 16, 2005.
    The commenter requests that the reference to the Swiss AD be 
changed to incorporate the new AD number.
    What is FAA's response to the concern? We concur with the commenter 
and will change the final rule AD action.
    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for the 
changes discussed above and minor editorial corrections. We have 
determined that these changes and minor corrections:

--Are consistent with the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Docket Information

    Where can I go to view the docket information? You may view the AD 
docket that contains information relating to this subject in person at 
the DMS Docket Offices between 9 a.m. and 5 p.m. (eastern standard 
time), Monday through Friday, except Federal holidays. The Docket 
Office (telephone 1-800-647-5227) is located on the plaza level of the 
Department of Transportation NASSIF Building at the street address 
stated in ADDRESSES. You may also view the AD docket on the Internet at 
http://dms.dot.gov.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002),

[[Page 47718]]

which governs the FAA's AD system. This regulation now includes 
material that relates to altered products, special flight permits, and 
alternative methods of compliance. This material previously was 
included in each individual AD. Since this material is included in 14 
CFR part 39, we will not include it in future AD actions.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 41 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to do the 
inspections:

----------------------------------------------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                  Parts cost           airplane          Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
11 work hours x $65 per hour =     Not applicable.....               $715  $715 x 41 = $29,315
 $715.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that will be required based on the results of the inspections. We have 
no way of determining the number of airplanes that may need these 
replacements:

----------------------------------------------------------------------------------------------------------------
                                                                        Total cost per airplane to replace all
               Labor cost                        Parts cost                             parts
----------------------------------------------------------------------------------------------------------------
10 work hours x $65 = $650.............  $2,000 to replace all       $650 + $2,000 = $2,650
                                          parts.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
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 AD.

Regulatory Findings

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD will not have a substantial direct effect on the States, on the 
relationship between the national government and the States, or on the 
distribution of power and responsibilities among the various levels of 
government.
    Will this AD involve a significant rule or regulatory action? 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 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 summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2005-17-01 Pilatus Aircraft Ltd.: Amendment 39-14221; Docket No. 
FAA-2005-20515; Directorate Identifier 2005-CE-09-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on September 29, 2005.

What Other ADs Are Affected By This Action?

    (b) None.

What Airplanes Are Affected by This AD?

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

    Note 1: These airplanes are also identified as Fairchild 
Republic Company PC-6 series airplanes and Fairchild Heli Porter PC-
6 series airplanes.


------------------------------------------------------------------------
                                 Models
-------------------------------------------------------------------------
(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
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Switzerland. We are issuing this AD to detect and correct cracks in 
the stabilizer-trim attachment and surrounding structural 
components, which could result in failure of the stabilizer-trim 
attachment. This failure could lead to loss of control of the 
airplane.

What Must I Do To Address This Problem?

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

[[Page 47719]]



------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the following:
(i) the stabilizer-trim       Within the next 100   Follow Pilatus PC-6
 attachment and structural     hours time-in-        Service Bulletin
 components (fitting,          service (TIS) after   No. 53-001, Rev.
 connecting piece, bearing     September 29, 2005    No. 1, dated June
 fork, bearing support         (the effective date   1, 2005.
 assembly, and auxiliary       of this AD).
 frame, as applicable) for     Repetitively
 cracks and corrosion; and.    inspect thereafter
(ii) the diameters of the      at intervals not-to-
 actuator attachment bolt      exceed 3,500 hours
 holes on the fittings,        TIS or 7 years,
 auxiliary frame, and          whichever occurs
 connecting piece (as          first.
 applicable) for
 discrepancies..
-----------------------------
(2) If cracks are found       Replace the           Follow Pilatus PC-6
 during any inspection         defective part        Service Bulletin
 required in paragraph         before further        No. 53-001, Rev.
 (e)(1)(i) of this AD,         flight after the      No. 1, dated June
 replace the defective part    inspection in which   1, 2005.
 with a new part.              cracks are found.
                               After each
                               replacement,
                               continue with the
                               repetitive
                               inspection
                               requirement in
                               paragraph (e)(1) of
                               this AD.
-----------------------------
(3) If corrosion or
 discrepancies are found
 during any inspection
 required in paragraphs
 (e)(1)(i) and (e)(1)(ii) of
 this AD, do the following:
(i) replace the defective     Replace or repair     Follow Pilatus PC-6
 part with a new part if the   the defective part    Service Bulletin
 corrosion or discrepancy is   before further        No. 53-001, Rev.
 beyond the repairable         flight after the      No. 1, dated June
 limits stated in the          inspection in which   1, 2005.
 service information; or.      corrosion or
(ii) repair the defective      discrepancies are
 part if the corrosion or      found. After each
 discrepancy is within the     replacement or
 repairable limits stated in   repair, continue
 the service information..     with the repetitive
                               inspection
                               requirement in
                               paragraph (e)(1) of
                               this AD.
-----------------------------
(4) Replace the following:
(i) all Fairchild connecting  Within the next 100   Follow Pilatus PC-6
 pieces, part number (P/N)     hours TIS after       Service Bulletin
 6232.0026.XX, with a          September 29, 2005    No. 53-001, Rev.
 Pilatus connecting piece, P/  (the effective date   No. 1, dated June
 N 6232.0026.XX. The           of this AD). After    1, 2005.
 Fairchild part has a rivet    replacement,
 in the middle that is not     repetitively
 on the Pilatus part; and.     inspect thereafter
(ii) all fittings, P/N         at intervals not-to-
 116.40.06.033 without an      exceed 3,500 hours
 index after the P/N, with     TIS or 7 years,
 an improved part, P/N         whichever occurs
 116.40.06.033 with an index   first. If after the
 of ``A'' or ``B'' after the   inspection required
 P/N or with P/N               in paragraph (e)(1)
 116.40.06.112..               of this AD, you
                               determine that you
                               already have a P/N
                               116.40.06.033 with
                               an index of ``A''
                               or ``B'' or a P/N
                               116.40.06.112
                               installed,
                               repetitively
                               inspect thereafter
                               at intervals not-to-
                               exceed 3,500 hours
                               TIS or 7 years,
                               whichever occurs
                               first after the
                               part was installed.
-----------------------------
(5) Do not install any of
 the following:
(i) Fairchild connecting      As of September 29,   Follow Pilatus PC-6
 piece, P/N 6232.0026.XX (it   2005 (the effective   Service Bulletin
 has a rivet in the middle     date of this AD).     No. 53-001, Rev.
 that is not on the Pilatus                          No. 1, dated June
 part); and.                                         1, 2005.
(ii) fitting, P/N
 116.40.06.033, without an
 index after the part
 number..
------------------------------------------------------------------------


    Note 2: Even though not required in this AD, the FAA recommends 
that you send all defective parts to Pilatus at the address 
specified in paragraph (h) of this AD. With the part, include the 
aircraft serial number, flying hours, and cycles.

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Standards Office, Small 
Airplane Directorate, FAA. For information on any already approved 
alternative methods of compliance, 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.

Is There Other Information That Relates to This Subject?

    (g) Swiss AD HB-2005-263, effective date June 16, 2005, also 
addresses the subject of this AD.

Does This AD Incorporate Any Material by Reference?

    (h) You must do the actions required by this AD following the 
instructions in Pilatus PC-6 Service Bulletin No. 53-001, Rev. No. 
1, dated June 1, 2005. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of 
this service information, contact Pilatus Aircraft Ltd., Customer 
Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 
6580; facsimile: +41 41 619 6576. To review copies of this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, go to: http://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. 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 20590-001 or on the Internet 
at http://dms.dot.gov. The docket number is FAA-2005-20515; 
Directorate Identifier 2005-CE-09-AD.


[[Page 47720]]


    Issued in Kansas City, Missouri, on August 8, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-16000 Filed 8-12-05; 8:45 am]
BILLING CODE 4910-13-P