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, 34401-34405 [05-11703]

Download as PDF 34401 Proposed Rules Federal Register Vol. 70, No. 113 Tuesday, June 14, 2005 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20515; Directorate Identifier 2005–CE–09–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), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); Reopening of the comment period. AGENCY: SUMMARY: The FAA proposes to revise an earlier proposed airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic Company and Fairchild Heli Porter) Model PC–6 airplanes. The earlier NPRM proposed to require 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. The earlier NPRM also proposed to require you to replace all Fairchild connecting pieces with a Pilatus connecting piece. The earlier NPRM resulted from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. This proposed AD would retain the actions from the earlier NPRM and would require you to replace fittings without an index after the part number (P/N) with an improved part. This proposed AD results from incorporating revised manufacture service information to include a procedure for replacing certain fittings with an improved part and to correct the allowable limits of the actuator attachment hole diameters. This proposed AD also clarifies the VerDate jul<14>2003 20:03 Jun 13, 2005 Jkt 205001 applicability. Since this action imposes an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on this additional action. DATES: We must receive any comments on this proposed AD by July 13, 2005. ADDRESSES: Use one of the following to submit comments on this proposed 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 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– 001. • Fax: 1–202–493–2251. • 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. To get the service information identified in this proposed 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 comments on this proposed AD, go to https://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: Comments Invited How do I comment on this proposed AD? We invite you to submit any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include the docket number, ‘‘FAA–2005–20515; Directorate Identifier 2005–CE–09–AD’’ at the beginning of your 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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket web site, anyone can find and read the comments received into any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). This is docket number FAA–2005–20515. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https:// dms.dot.gov. Are there any specific portions of this proposed AD I should pay attention to? We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. If you contact us through a nonwritten communication and that contact relates to a substantive part of this proposed AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend this proposed AD in light of those comments and contacts. Docket Information Where can I go to view the docket information? You may view the AD docket that contains this proposal, any comments received, and any final disposition 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 https://dms.dot.gov. The comments will be available in the AD docket shortly after the DMS receives them. Discussion What is the background of the subject matter? 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. E:\FR\FM\14JNP1.SGM 14JNP1 34402 Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Proposed Rules 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 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. Was the public invited to comment? The FAA encouraged interested persons to participate in developing this amendment. The following presents the comments received on the proposal and FAA’s response to each comment: Comment Issue No. 1: Incorporate Revised Service Bulletin What is the commenter’s concern? Pilatus has revised the original service bulletin to include a requirement to replace fittings, part number (P/N) 116.40.06.033 without an index of ‘‘A’’ or ‘‘B’’ with an improved part, P/N 116.40.06.112. Pilatus Service Bulletin No. 147, dated May 1985, requires you to inspect P/N 116.40.06.033 for cracks and to replace all cracked P/Ns 116.40.06.033 with an improved part, P/N 116.40.06.112. If no cracks are found, P/ N 116.40.06.033 without an index of ‘‘A’’ or ‘‘B’’ can remain installed provided it is repetitively inspected for cracks every 100 hours time-in-service (TIS). Pilatus Service Bulletin No. 147, dated May 1985, states that P/N 116.40.06.033 with an Index A is not subject to the 100-hour repetitive inspection. VerDate jul<14>2003 20:03 Jun 13, 2005 Jkt 205001 Pilatus PC–6 Service Bulletin No. 53– 001, Rev. No. 1, dated June 1, 2005, terminates the 100-hour repetitive inspection specified in Service Bulletin No. 147. The 100-hour repetitive inspection is terminated by requiring you to replace all P/Ns 116.40.06.033 without an index of ‘‘A’’ or ‘‘B’’ with an improved part, P/N 116.40.04.112. Pilatus requests the actions in the revised service bulletin be included in the proposed AD action. What is FAA’s response to the concern? We agree with the commenter. It is FAA’s policy that reliance on critical repetitive inspections on airplanes utilized in commuter service for hire carries an unnecessary safety risk when a design change exists that could eliminate or, in certain instances, reduce the number of those critical inspections. In determining what inspections are critical, the FAA considers (1) The safety consequences of the airplane if the known problem is not detected by the inspection; (2) the reliability of the inspection such as the probability of not detecting the known problem; (3) whether the inspection area is difficult to access; and (4) the possibility of damage to an adjacent structure as a result of the problem. The fitting is considered a critical structural component. Requiring replacement of all P/Ns 116.40.06.033 without an index of ‘‘A’’ or ‘‘B’’ with a P/N 116.40.06.112 terminates the 100hour repetitive inspection specified in Pilatus Service Bulletin No. 147, dated May 1985. We have confirmed with Pilatus that replacing P/Ns 116.40.06.033 without an index of ‘‘A’’ or ‘‘B’’ with a P/N 116.40.06.033 with an index of ‘‘A’’ or ‘‘B’’ also terminates the 100-hour repetitive inspection specified in Pilatus Service Bulletin No. 147, dated May 1985. Since a design change exists that reduces the number of critical inspections, we will change this proposed AD to include this action. Including this action imposes an additional burden over that proposed in the earlier NPRM. We are reopening the comment period to allow the public the opportunity to comment on this additional action. Comment Issue No. 2: Change the Repetitive Inspection Intervals What is the commenter’s concern? The commenter states that repetitive dye-penetrant inspection of all affected parts at 100-hour TIS intervals could cause more damage. Dye-penetrant inspections require considerable paint stripping. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 The Aircraft Maintenance Manual (AMM) for these airplanes currently requires a repetitive dye-penetrant inspection on the affected parts every 3,500 hours TIS or every 7 years, whichever occurs first. The commenter requests the repetitive inspection intervals be changed to every 3,500 hours TIS or every 7 years, whichever occurs first, to coincide with the AMM. What is FAA’s response to the concern? We agree that the repetitive 100-hour TIS inspections could cause additional damage to the affected parts. The FAA’s intent was to mandate the repetitive inspections of the AMM. The NPRM inadvertently carried 100 hours TIS as the repetitive interval. The correct interval for the repetitive inspection is 3,500 hours TIS. The AMM specifies the inspection every 3,500 hours TIS or every 7 years, whichever occurs first. However, the only way we can ensure that all operators follow this AMM specification is through an AD. Therefore, we will make this change in the proposed AD action to ensure the inspections are done. Comment Issue No. 3: Clarify the Applicability of the Affected Airplanes What is the commenter’s concern? A commenter states that it is not clear whether the proposed AD applied to Fairchild built Model PC–6 airplanes or to both Pilatus and Fairchild built Model PC–6 airplanes. Also, it is unclear whether the proposed AD applies only to Model PC– 6 airplanes or to all PC–6 series airplanes. The commenter requests clarification on the applicability of the affected airplanes. What is FAA’s response to the concern? We agree with commenter that the applicability may be unclear. Fairchild Republic Company and Fairchild Heli Porter manufactured certain Model PC–6 airplanes under the license agreement shown on the United States (U.S.) type certificate data sheet (TCDS) No. 7A15, which is currently held by Pilatus Aircraft Ltd. This proposed AD applies to all PC– 6 series airplanes, including those built by Fairchild Republic Company and Fairchild Heli Porter. We will change the proposed AD action to clarify the applicability. What events have caused FAA to issue a supplemental NPRM? In addition to the changes noted above, the manufacturer revised the service information to include a requirement for replacing the fitting without an index after the part number with an improved E:\FR\FM\14JNP1.SGM 14JNP1 34403 Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Proposed Rules part and to correct the allowable limits of the actuator attachment hole diameters. FAA’s Determination and Requirements of This Proposed AD What has FAA decided? After examining the circumstances and reviewing all available information related to the incidents described above, we have determined that: —The unsafe condition referenced in this document exists or could develop on other Pilatus Model PC–6 airplanes of the same type design that are on the U.S. registry; —We should change the NPRM to incorporate the concerns addressed by the commenters and incorporate the revised service information; and —We should take AD action to correct this unsafe condition. The Supplemental NPRM How will the changes to the NPRM impact the public? Proposing to require you to replace fittings without an index after the part number with a different part goes beyond the scope of what was originally proposed in the NPRM. Therefore, we are reopening the comment period and allowing the public the chance to comment on these additional actions. What are the provisions of the supplemental NPRM? The proposed AD would 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; —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. How does the revision to 14 CFR part 39 affect this proposed AD? On July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs 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 would this proposed AD impact? We estimate that this proposed AD affects 41 airplanes in the U.S. registry. What would be the cost impact of this proposed AD on owners/operators of the affected airplanes? We estimate the following costs to do the proposed inspections: Total cost per airplane Labor cost Parts cost 11 work hours × $65 per hour = $715 ........................................... Total cost on U.S. operators $715 $715 × 41 = $29,315. Not applicable ............................ We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspections. We have no way of determining the number of airplanes that may need these replacements: Total cost per airplane to replace all parts Labor cost Parts cost 10 work hours × $65 = $650 ............................................ $2,000 to replace all parts .............................................. Authority for This Rulemaking Regulatory Findings 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. Would this proposed AD impact various entities? 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. Would this proposed AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this proposed AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities VerDate jul<14>2003 20:03 Jun 13, 2005 Jkt 205001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 $650 + $2,000 = $2,650. under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this proposed 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 ‘‘AD Docket 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: E:\FR\FM\14JNP1.SGM 14JNP1 34404 Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Proposed Rules PART 39—AIRWORTHINESS DIRECTIVES What Other ADs Are Affected By This Action? (b) None. 1. The authority citation for part 39 continues to read as follows: 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. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Pilatus Aircraft Ltd.: Docket No. FAA–2005– 20515; Directorate Identifier 2005–CE– 09–AD. When is the Last Date I Can Submit Comments on This Proposed AD? (a) We must receive comments on this proposed airworthiness directive (AD) by July 13, 2005. 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 Actions (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 proposed 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: 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.. Procedures Within the next 100 hours time-in-service (TIS) after the effective date of this AD. Repetitively inspect thereafter at intervals notto-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 the effective date of this AD. After replacement, repetitively inspect thereafter at intervals notto-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-toexceed 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 the effective date of this AD ................... Follow Pilatus PC–6 Service Bulletin No. 53– 001, Rev. No. 1, dated June 1, 2005. . (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 VerDate jul<14>2003 22:28 Jun 13, 2005 Jkt 205001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\14JNP1.SGM 14JNP1 Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Proposed Rules 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 (g) of this AD. With the part, include the aircraft serial number, flying hours, and cycles. May I Request an Alternative Method of Compliance? Is There Other Information That Relates to This Subject? (g) Swiss AD HB–2005–080, effective date March 2, 2005, also addresses the subject of this AD. The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, classified Pilatus PC–6 Service Bulletin No. 53–001, Rev. No. 1, dated June 1, 2005, as mandatory. The FAA anticipates that the FOCA will issue a new Swiss AD in order to ensure the continued airworthiness of these airplanes in Switzerland. May I Get Copies of the Documents Referenced in This AD? (h) You may get copies of the documents referenced in this AD from 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, or on the Internet at https://dms.dot.gov. The docket number is FAA–2005–20515. Issued in Kansas City, Missouri, on June 7, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11703 Filed 6–13–05; 8:45 am] VerDate jul<14>2003 20:03 Jun 13, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21434; Directorate Identifier 2004–NM–75–AD] RIN 2120–AA64 (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. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Airworthiness Directives; Boeing Model 727 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This proposed AD would require repetitive inspections for cracks of the body skin, doubler, and bear strap at the forward edge of the upper and lower hinge cutouts of the forward entry door, related investigative actions, and corrective action if necessary. This proposed AD also would require a preventive modification. This proposed AD is prompted by reports of skin and bear strap cracks at hinge cutouts. We are proposing this AD to detect and correct cracks in the skin and bear strap at the hinge cutouts of the forward entry door, which could result in rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by July 29, 2005. ADDRESSES: Use one of the following addresses to submit comments 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. • By 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You may examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or at the Docket Management Facility, U.S. Department PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 34405 of Transportation, 400 Seventh Street, SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW. Renton, Washington 98055–4056; telephone (425) 917–6456; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21434; Directorate Identifier 2004NM–75-AD’’ in the subject line 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 submitted 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 with FAA personnel concerning this proposed AD. Using the search function of that website, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion We have received reports from 12 operators of skin cracks in the forward entry door cutouts on 75 Boeing Model 727 airplanes. The cracks were detected or found on airplanes that had accumulated between 19,500 and 65,500 E:\FR\FM\14JNP1.SGM 14JNP1

Agencies

[Federal Register Volume 70, Number 113 (Tuesday, June 14, 2005)]
[Proposed Rules]
[Pages 34401-34405]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11703]

========================================================================
Proposed Rules
Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

========================================================================

Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 /
Proposed Rules

[[Page 34401]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20515; Directorate Identifier 2005-CE-09-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), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); Reopening of
the comment period.

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

SUMMARY: The FAA proposes to revise an earlier proposed airworthiness
directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus)
(also identified as Fairchild Republic Company and Fairchild Heli
Porter) Model PC-6 airplanes. The earlier NPRM proposed to require 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. The earlier NPRM also proposed to
require you to replace all Fairchild connecting pieces with a Pilatus
connecting piece. The earlier NPRM resulted from mandatory continuing
airworthiness information (MCAI) issued by the airworthiness authority
for Switzerland. This proposed AD would retain the actions from the
earlier NPRM and would require you to replace fittings without an index
after the part number (P/N) with an improved part. This proposed AD
results from incorporating revised manufacture service information to
include a procedure for replacing certain fittings with an improved
part and to correct the allowable limits of the actuator attachment
hole diameters. This proposed AD also clarifies the applicability.
Since this action imposes an additional burden over that proposed in
the NPRM, we are reopening the comment period to allow the public the
chance to comment on this additional action.

DATES: We must receive any comments on this proposed AD by July 13,
2005.

ADDRESSES: Use one of the following to submit comments 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 20590-001.
Fax: 1-202-493-2251.
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.
To get the service information identified in this proposed 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 comments on this proposed AD, go to https://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:

Comments Invited

How do I comment on this proposed AD? We invite you to submit any
written relevant data, views, or arguments regarding this proposal.
Send your comments to an address listed under ADDRESSES. Include the
docket number, ``FAA-2005-20515; Directorate Identifier 2005-CE-09-AD''
at the beginning of your 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 with FAA personnel concerning this proposed
rulemaking. Using the search function of our docket web site, anyone
can find and read the comments received into any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
This is docket number FAA-2005-20515. You may review the DOT's complete
Privacy Act Statement in the Federal Register published on April 11,
2000 (65 FR 19477-78) or you may visit https://dms.dot.gov.
Are there any specific portions of this proposed AD I should pay
attention to? We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of this
proposed AD. If you contact us through a nonwritten communication and
that contact relates to a substantive part of this proposed AD, we will
summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend this
proposed AD in light of those comments and contacts.

Docket Information

Where can I go to view the docket information? You may view the AD
docket that contains this proposal, any comments received, and any
final disposition 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 https://dms.dot.gov. The comments will
be available in the AD docket shortly after the DMS receives them.

Discussion

What is the background of the subject matter? 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.

[[Page 34402]]

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.

Was the public invited to comment? The FAA encouraged interested
persons to participate in developing this amendment. The following
presents the comments received on the proposal and FAA's response to
each comment:

Comment Issue No. 1: Incorporate Revised Service Bulletin

What is the commenter's concern? Pilatus has revised the original
service bulletin to include a requirement to replace fittings, part
number (P/N) 116.40.06.033 without an index of ``A'' or ``B'' with an
improved part, P/N 116.40.06.112.
Pilatus Service Bulletin No. 147, dated May 1985, requires you to
inspect P/N 116.40.06.033 for cracks and to replace all cracked P/Ns
116.40.06.033 with an improved part, P/N 116.40.06.112. If no cracks
are found, P/N 116.40.06.033 without an index of ``A'' or ``B'' can
remain installed provided it is repetitively inspected for cracks every
100 hours time-in-service (TIS).
Pilatus Service Bulletin No. 147, dated May 1985, states that P/N
116.40.06.033 with an Index A is not subject to the 100-hour repetitive
inspection.
Pilatus PC-6 Service Bulletin No. 53-001, Rev. No. 1, dated June 1,
2005, terminates the 100-hour repetitive inspection specified in
Service Bulletin No. 147. The 100-hour repetitive inspection is
terminated by requiring you to replace all P/Ns 116.40.06.033 without
an index of ``A'' or ``B'' with an improved part, P/N 116.40.04.112.
Pilatus requests the actions in the revised service bulletin be
included in the proposed AD action.
What is FAA's response to the concern? We agree with the commenter.
It is FAA's policy that reliance on critical repetitive inspections
on airplanes utilized in commuter service for hire carries an
unnecessary safety risk when a design change exists that could
eliminate or, in certain instances, reduce the number of those critical
inspections. In determining what inspections are critical, the FAA
considers (1) The safety consequences of the airplane if the known
problem is not detected by the inspection; (2) the reliability of the
inspection such as the probability of not detecting the known problem;
(3) whether the inspection area is difficult to access; and (4) the
possibility of damage to an adjacent structure as a result of the
problem.
The fitting is considered a critical structural component.
Requiring replacement of all P/Ns 116.40.06.033 without an index of
``A'' or ``B'' with a P/N 116.40.06.112 terminates the 100-hour
repetitive inspection specified in Pilatus Service Bulletin No. 147,
dated May 1985.
We have confirmed with Pilatus that replacing P/Ns 116.40.06.033
without an index of ``A'' or ``B'' with a P/N 116.40.06.033 with an
index of ``A'' or ``B'' also terminates the 100-hour repetitive
inspection specified in Pilatus Service Bulletin No. 147, dated May
1985.
Since a design change exists that reduces the number of critical
inspections, we will change this proposed AD to include this action.
Including this action imposes an additional burden over that
proposed in the earlier NPRM. We are reopening the comment period to
allow the public the opportunity to comment on this additional action.

Comment Issue No. 2: Change the Repetitive Inspection Intervals

What is the commenter's concern? The commenter states that
repetitive dye-penetrant inspection of all affected parts at 100-hour
TIS intervals could cause more damage. Dye-penetrant inspections
require considerable paint stripping.
The Aircraft Maintenance Manual (AMM) for these airplanes currently
requires a repetitive dye-penetrant inspection on the affected parts
every 3,500 hours TIS or every 7 years, whichever occurs first.
The commenter requests the repetitive inspection intervals be
changed to every 3,500 hours TIS or every 7 years, whichever occurs
first, to coincide with the AMM.
What is FAA's response to the concern? We agree that the repetitive
100-hour TIS inspections could cause additional damage to the affected
parts. The FAA's intent was to mandate the repetitive inspections of
the AMM. The NPRM inadvertently carried 100 hours TIS as the repetitive
interval. The correct interval for the repetitive inspection is 3,500
hours TIS.
The AMM specifies the inspection every 3,500 hours TIS or every 7
years, whichever occurs first. However, the only way we can ensure that
all operators follow this AMM specification is through an AD.
Therefore, we will make this change in the proposed AD action to ensure
the inspections are done.

Comment Issue No. 3: Clarify the Applicability of the Affected
Airplanes

What is the commenter's concern? A commenter states that it is not
clear whether the proposed AD applied to Fairchild built Model PC-6
airplanes or to both Pilatus and Fairchild built Model PC-6 airplanes.
Also, it is unclear whether the proposed AD applies only to Model
PC-6 airplanes or to all PC-6 series airplanes.
The commenter requests clarification on the applicability of the
affected airplanes.
What is FAA's response to the concern? We agree with commenter that
the applicability may be unclear.
Fairchild Republic Company and Fairchild Heli Porter manufactured
certain Model PC-6 airplanes under the license agreement shown on the
United States (U.S.) type certificate data sheet (TCDS) No. 7A15, which
is currently held by Pilatus Aircraft Ltd.
This proposed AD applies to all PC-6 series airplanes, including
those built by Fairchild Republic Company and Fairchild Heli Porter.
We will change the proposed AD action to clarify the applicability.
What events have caused FAA to issue a supplemental NPRM? In
addition to the changes noted above, the manufacturer revised the
service information to include a requirement for replacing the fitting
without an index after the part number with an improved

[[Page 34403]]

part and to correct the allowable limits of the actuator attachment
hole diameters.

FAA's Determination and Requirements of This Proposed AD

What has FAA decided? After examining the circumstances and
reviewing all available information related to the incidents described
above, we have determined that:
--The unsafe condition referenced in this document exists or could
develop on other Pilatus Model PC-6 airplanes of the same type design
that are on the U.S. registry;
--We should change the NPRM to incorporate the concerns addressed by
the commenters and incorporate the revised service information; and
--We should take AD action to correct this unsafe condition.

The Supplemental NPRM

How will the changes to the NPRM impact the public? Proposing to
require you to replace fittings without an index after the part number
with a different part goes beyond the scope of what was originally
proposed in the NPRM. Therefore, we are reopening the comment period
and allowing the public the chance to comment on these additional
actions.
What are the provisions of the supplemental NPRM? The proposed AD
would 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;
--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.
How does the revision to 14 CFR part 39 affect this proposed AD? On
July 10, 2002, we published a new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs 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 would this proposed AD impact? We estimate that
this proposed AD affects 41 airplanes in the U.S. registry.
What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to
do the proposed inspections:

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

We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed
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 parts.. $650 + $2,000 = $2,650.
----------------------------------------------------------------------------------------------------------------

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

Would this proposed AD impact various entities? 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.
Would this proposed AD involve a significant rule or regulatory
action? For the reasons discussed above, I certify that this proposed
AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this proposed 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
``AD Docket 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, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:

[[Page 34404]]

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 adding the following new
airworthiness directive (AD):

Pilatus Aircraft Ltd.: Docket No. FAA-2005-20515; Directorate
Identifier 2005-CE-09-AD.

When is the Last Date I Can Submit Comments on This Proposed AD?

(a) We must receive comments on this proposed airworthiness
directive (AD) by July 13, 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 proposed 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:

------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the following:
(i) the stabilizer-trim Within the next Follow Pilatus PC-
attachment and structural 100 hours time-in- 6 Service
components (fitting, service (TIS) Bulletin No. 53-
connecting piece, bearing after the 001, Rev. No. 1,
fork, bearing support effective date of dated June 1,
assembly, and auxiliary this AD. 2005.
frame, as applicable) for Repetitively
cracks and corrosion; and. inspect
(ii) the diameters of the thereafter at
actuator attachment bolt intervals not-to-
holes on the fittings, exceed 3,500
auxiliary frame, and hours TIS or 7
connecting piece (as years, whichever
applicable) for occurs first.
discrepancies.
---------------------------------
(2) If cracks are found during Replace the Follow Pilatus PC-
any inspection required in defective part 6 Service
paragraph (e)(1)(i) of this AD, before further Bulletin No. 53-
replace the defective part with flight after the 001, Rev. No. 1,
a new part. inspection in dated June 1,
which cracks are 2005.
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-
part with a new part if the the defective 6 Service
corrosion or discrepancy is part before Bulletin No. 53-
beyond the repairable further flight 001, Rev. No. 1,
limits stated in the after the dated June 1,
service information; or. inspection in 2005.
(ii) repair the defective which corrosion
part if the corrosion or or discrepancies
discrepancy is within the are found. After
repairable limits stated in each replacement
the service information.. or repair,
continue with the
repetitive
inspection
requirement in
paragraph (e)(1)
of this AD.
---------------------------------

---------------------------------
(4) Replace the following:
(i) all Fairchild connecting Within the next Follow Pilatus PC-
pieces, part number (P/N) 100 hours TIS 6 Service
6232.0026.XX, with a after the Bulletin No. 53-
Pilatus connecting piece, P/ effective date of 001, Rev. No. 1,
N 6232.0026.XX. The this AD. After dated June 1,
Fairchild part has a rivet replacement, 2005.
in the middle that is not repetitively
on the Pilatus part; and. inspect
(ii) all fittings, P/N thereafter at
116.40.06.033 without an intervals not-to-
index after the P/N, with exceed 3,500
an improved part, P/N hours TIS or 7
116.40.06.033 with an index years, whichever
of ``A'' or ``B'' after the occurs first. If
P/N or with P/N after the
116.40.06.112. 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.
---------------------------------
(5) Do not install any of the
following:
(i) Fairchild connecting As of the Follow Pilatus PC-
piece, P/N 6232.0026.XX (it effective date of 6 Service
has a rivet in the middle this AD. Bulletin No. 53-
that is not on the Pilatus 001, Rev. No. 1,
part); and. dated June 1,
(ii) fitting, P/N 2005.
116.40.06.033, without an
index after the part number.
------------------------------------------------------------------------

[[Page 34405]]

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 (g) 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-2005-080, effective date March 2, 2005, also
addresses the subject of this AD. The Federal Office for Civil
Aviation (FOCA), which is the airworthiness authority for
Switzerland, classified Pilatus PC-6 Service Bulletin No. 53-001,
Rev. No. 1, dated June 1, 2005, as mandatory. The FAA anticipates
that the FOCA will issue a new Swiss AD in order to ensure the
continued airworthiness of these airplanes in Switzerland.

May I Get Copies of the Documents Referenced in This AD?

(h) You may get copies of the documents referenced in this AD
from 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, or on the Internet at https://
dms.dot.gov. The docket number is FAA-2005-20515.

Issued in Kansas City, Missouri, on June 7, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-11703 Filed 6-13-05; 8:45 am]
BILLING CODE 4910-13-P

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