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, 26891-26894 [E6-7017]

Download as PDF Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules part number of the ailerons. For airplanes with affected aileron part numbers, the proposed AD would have required reworking the aileron damper fitting, and for certain airplanes, replacing the rod end of the aileron damper assembly with an improved rod end. Since the proposed AD was issued, we have received new data indicating that there is no unsafe condition associated with structural failure of the rod end of the aileron damper. Accordingly, the proposed AD is withdrawn. You may examine the AD docket on the Internet at https:// dms.dot.gov, or 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 U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Washington, DC. This docket number is FAA–2006–23673; the directorate identifier for this docket is 2005–NM– 233–AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. ADDRESSES: SUPPLEMENTARY INFORMATION: mstockstill on PROD1PC68 with PROPOSALS Discussion We proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with a notice of proposed rulemaking (NPRM) for a new AD for all EMBRAER Model EMB–135 and EMB– 145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. That NPRM was published in the Federal Register on January 25, 2006 (71 FR 4067). The NPRM would have required inspecting to determine the part number of the ailerons. For airplanes with affected aileron part numbers, the NPRM would have required reworking the aileron damper fitting. Also, for certain airplanes, the NPRM would have required replacing the rod end of the aileron damper assembly with an improved rod end. The NPRM resulted from reports of structural failure of the rod end of the aileron damper, which was caused by insufficient clearance between the lugs of the aileron damper fitting and the rod end of the aileron damper. The proposed actions were intended to prevent failure of the aileron damper, which could result in failure of the aileron actuator and VerDate Aug<31>2005 15:37 May 08, 2006 Jkt 208001 consequent reduced controllability of the airplane. Comments EMBRAER requests that we withdraw the NPRM. EMBRAER points out that the unsafe condition stated in the NPRM (failure of the aileron damper, which could result in failure of the aileron actuator and consequent reduced controllability of the airplane) is incorrect. While the NPRM was intended to address reports of structural failure of the rod end of the aileron damper, there is no unsafe condition caused by such a failure. The aileron damper was introduced to improve safety by increasing redundancy: the aileron damper prevents vibration of the aileron surface in the event of failure of both rods of the aileron power control actuator (PCA). Failure of the rod end of the aileron damper and subsequent failure of the aileron damper will not cause vibration of the aileron surface. Further, while failure of the rod ends of the aileron PCA could result in reduced controllability of the airplane, this unsafe condition is already addressed by another action. EMBRAER notes that the FAA has previously issued AD 99–05–04 (64 FR 13894, March 23, 1999). That AD requires inspections to detect and correct cracking or failure of the rod ends of the aileron PCA on all EMBRAER Model EMB–145 series airplanes. EMBRAER further states that repetitive inspections of the aileron damper rod ends and fitting lugs for integrity and general condition are specified as a Certification Maintenance Requirement (for Model EMB–135 airplanes) and a System Inspection Requirement (for Model EMB–145 airplanes). The failures of the aileron damper rod ends that prompted the NRPM were discovered during inspections performed under these requirements. We agree with the commenter’s request to withdraw the NPRM. EMBRAER Service Bulletin 145–27– 0108, Revision 01, dated April 28, 2005, which the NPRM references as the appropriate source of service information for the required actions, was issued to correct insufficient clearance between the lugs of the aileron damper fitting and the rod end of the aileron damper. We have coordinated with EMBRAER and have determined that the actions in that service bulletin are not intended to address an unsafe condition. Doing those actions may provide an economic benefit to operators by preventing the need for an expensive repair in the event that damage is detected during PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 26891 routine inspections. Since there is no unsafe condition, the proposed AD is unnecessary. FAA’s Conclusions Upon further consideration, we have determined that there is no unsafe condition associated with structural failure of the rod end of the aileron damper. Accordingly, the NPRM is withdrawn. Withdrawal of the NPRM does not preclude the FAA from issuing another related action or commit the FAA to any course of action in the future. Regulatory Impact Since this action only withdraws an NPRM, it is neither a proposed nor a final rule and therefore is not covered under Executive Order 12866, the Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Withdrawal Accordingly, we withdraw the NPRM, Docket No. FAA–2006–23673, Directorate Identifier 2005–NM–233– AD, which was published in the Federal Register on January 25, 2006 (71 FR 4067). Issued in Renton, Washington, on April 28, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–7015 Filed 5–8–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24092; Directorate Identifier 2006–CE–18–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC– 6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1–H2 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: E:\FR\FM\09MYP1.SGM 09MYP1 mstockstill on PROD1PC68 with PROPOSALS 26892 Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003–09– 01, which applies to Pilatus Aircraft Ltd (Pilatus) Model PC–6 airplanes, all manufacturer serial numbers (MSN) up to and including 939. AD 2003–09–01 currently requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. Since we issued AD 2003–09–01, the FAA determined the action should also apply to all the models of the PC–6 airplanes listed in the type certification data sheet of Type Certificate (TC) No. 7A15 that are produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 2003–09–01 was to all the affected serial numbers of the airplane models listed in TC No. 7A15. Consequently, this proposed AD would retain all the actions of AD 2003–09–01, would add those Fairchild Republic Company airplanes to the applicability of this proposed AD, and would list out the individual specific airplane models. We are proposing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight. DATES: We must receive comments on this proposed AD by June 9, 2006. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • DOT Docket Web site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; VerDate Aug<31>2005 15:37 May 08, 2006 Jkt 208001 telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2006–24092; Directorate Identifier 2006–CE–18–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion Mandatory continuing airworthiness information and the FAA’s determination that an unsafe condition existed on a Pilatus Model PC–6 airplane caused us to issue AD 2003– 09–01, Amendment 39–13130 (68 FR 22582, April 29, 2003). AD 2003–09–01 currently requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations on Pilatus Model PC– 6 airplanes. The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, notified the FAA of the need to supersede AD 2003– 09–01 to address an unsafe condition that may exist or could develop on Model PC–6 airplanes, all manufacturer serial numbers (MSN) up to and including 939. The FOCA reports that the AD action should also apply to all the models of the PC–6 airplanes listed in the type certification data sheet of TC No. 7A15 produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 This condition, if not corrected, could result in increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight. Foreign Airworthiness Authority Information The FOCA recently issued Swiss AD Number HB 2005–289, effective date August 23, 2005, to ensure the continued airworthiness of all models of the PC–6 airplanes listed in TC No. 7A15, including those produced in the United States under a licensing agreement with Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). The State of Design for the Pilatus PC–6 airplanes is Switzerland and the airplanes are type-certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the FOCA has kept us informed of the situation described above. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we have examined the FOCA’s findings, evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design that are certificated for operation in the United States. This proposed AD would supersede AD 2003–09–01 with a new AD that would retain all the actions of AD 2003– 09–01 and would: • Add manufacturer serial numbers (MSN) 2001 through 2092 for all the models of the PC–6 airplanes as listed in TC No. 7A15 and specified in the applicability section. These MSN are the airplanes produced in the United States through a licensing agreement with the Fairchild Republic Company; and • List all the models of the PC–6 airplanes as listed in TC No. 7A15. Costs of Compliance We estimate that this proposed AD would affect 49 airplanes in the U.S. registry. We estimate the following costs to do the proposed inspection and modifications: E:\FR\FM\09MYP1.SGM 09MYP1 26893 Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules Labor cost Parts cost Total cost per airplane 7 work hours × $80 per hour = $560 ..................................................................................... $300 $860 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, Pilatus Aircraft LTD.: Docket No. FAA– 2006–24092; Directorate Identifier 2006– CE–18–AD. Examining the AD Docket Affected ADs (b) This AD supersedes AD 2003–09–01, Amendment 39–13130. You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at https://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2003–09–01, Amendment 39–13130, and adding the following new AD: mstockstill on PROD1PC68 with PROPOSALS Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by June 9, 2006. Applicability (c) This AD affects the following 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 that are equipped with turbo-prop engines and are certificated in any category: (1) Group 1 (maintains the actions from AD 2003–09–01): All manufacturer serial numbers (MSN) up to and including 939. (2) Group 2: MSN 2001 through 2092. Note: These airplanes are also identified as Fairchild Republic Company PC–6 airplanes, Fairchild Heli Porter PC–6 airplanes, or Fairchild-Hiller Corporation PC–6 airplanes. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland that requires retaining the actions of AD 2003–09–01 and adding MSN 2001 through 2092 for all the models of the PC–6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15. We are issuing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight. Compliance (e) To address this problem, you must do the following: Compliance Procedures (1) Inspect, before removal of the wing (A) For Group 1 Airplanes: Within the next bellcrank assemblies, part numbers (P/N) 100 hours time-in-service (TIS) after June 6132.0071.51 and 6132.0071.52, for installed 17, 2003 (the effective date of AD 2003– circlips, P/N N237: 09–01), unless already done. (i) If circlips are installed, do the actions re- (B) For Group 2 Airplanes: Within the next quired in paragraphs (e)(5) and (e)(6) of 100 hours TIS after the effective date of this AD. this AD, unless already done. (ii) If circlips are not installed, perform all actions required by paragraphs (e)(3), (e)(4), (e)(5), (e)(6), and (e)(7) of this AD. 15:37 May 08, 2006 Jkt 208001 $860 × 49 = $42,140. on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. Actions VerDate Aug<31>2005 Total cost on U.S. operators PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. E:\FR\FM\09MYP1.SGM 09MYP1 26894 Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules Actions Compliance Procedures (2) Inspect, before removal of the fuselage bellcrank assembly, P/N 6232.0118.00, for the circlip installed on the housing to prevent axial movement of the bellcrank on its bearing and the flange of the housing to the rear. If the fuselage bellcrank assembly has either no circlip and/or it is not installed as required, perform the actions in paragraphs (e)(8) and (e)(9) of this AD. (3) Remove the wing bellcrank assemblies, P/ Ns 6132.0071.51 and 6132.0071.52, and inspect for worn or damaged bearings. Replace worn or damaged bearings. (4) Stake and lock the bearing in the housing of the wing bellcranks, P/Ns 6132.0071.51 and 6132.0071.52. (5) Inspect the wing bellcranks control-cable attachment bolts for correct type and for signs of rub damage on the heads. Replace bolts that are damaged and/or have a total length (including head) of more than 21.5 mm (0.85 in.) (6) Inspect the wing bellcranks support plate for signs of rub damage caused by the bolts. If damage is found: (i) Obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme. (7) Reinstall wing bellcrank assemblies ............. Before further flight after the inspection required in paragraph (e)(1) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1), (e)(2) and (e)(8) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. (8) Remove the fuselage bellcrank assembly, P/N 6232.0118.00, and inspect the housing for wear, damage, and signs of axial movement of the bearing in the housing. Replace worn or damaged bearings. If any signs of axial movement of a bearing are found: (i) Obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme. (9) Reinstall the fuselage bellcrank assembly. Ensure that the fuselage bellcrank assembly is installed so that the surface of the bellcrank with the flange of the housing is installed to the rear. The effect of this is to lock the bellcrank on the bearing tube and thus prevent movement. (10) Do not install any bellcrank assemblies, P/ Ns 6132.0071.51, 6132,0071.52, and 6232.0118.00 (or FAA-approved equivalent part numbers), unless the aileron assembly has been inspected, modified, and installed. mstockstill on PROD1PC68 with PROPOSALS Note 1: Axial movement of serviceable bearings in the housings of the wing bellcranks is permitted provided no wear or damage to the bearing is found. Note 2: Any signs of axial movement of a bearing in the housing of the fuselage bellcrank assembly requires that you obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD and incorporate the repair scheme. Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace Engineer, FAA, VerDate Aug<31>2005 15:37 May 08, 2006 Jkt 208001 Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. (A) For Group 1 Airplanes: As of June 17, Follow Pilatus Aircraft Ltd. PC–6 Service Bul2003 (the effective date of AD 2003–09–01). letin No. 27–001, dated June 5, 2002. (B) For Group 2 Airplanes: As of the effective date of this AD. Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; facsimile: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 2003–09–01 are approved for this AD. Related Information (h) To get copies of the documents referenced in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at https://dms.dot.gov. The docket number is Docket No. FAA–2006–24092; Directorate Identifier 2006–CE–18–AD. Issued in Kansas City, Missouri, on May 3, 2006. Barry R. Ballenger, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–7017 Filed 5–8–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\09MYP1.SGM 09MYP1

Agencies

[Federal Register Volume 71, Number 89 (Tuesday, May 9, 2006)]
[Proposed Rules]
[Pages 26891-26894]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-7017]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD]
RIN 2120-AA64

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

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

ACTION: Notice of proposed rulemaking (NPRM).

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

[[Page 26892]]

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003-09-
01, which applies to Pilatus Aircraft Ltd (Pilatus) Model PC-6
airplanes, all manufacturer serial numbers (MSN) up to and including
939. AD 2003-09-01 currently requires you to inspect and correct, as
necessary, the aileron control bellcrank assemblies at the wing and
fuselage locations. Since we issued AD 2003-09-01, the FAA determined
the action should also apply to all the models of the PC-6 airplanes
listed in the type certification data sheet of Type Certificate (TC)
No. 7A15 that are produced in the United States through a licensing
agreement between Pilatus and Fairchild Republic Company (also
identified as Fairchild Industries, Fairchild Heli Porter, or
Fairchild-Hiller Corporation). In addition, the intent of the
applicability of AD 2003-09-01 was to all the affected serial numbers
of the airplane models listed in TC No. 7A15. Consequently, this
proposed AD would retain all the actions of AD 2003-09-01, would add
those Fairchild Republic Company airplanes to the applicability of this
proposed AD, and would list out the individual specific airplane
models. We are proposing this AD to detect and correct increased
friction in the aileron control bellcrank assemblies, which could
result in failure of the aileron flight-control system. Such failure
could lead to problems in controlling flight.

DATES: We must receive comments on this proposed AD by June 9, 2006.

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

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

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-24092; Directorate Identifier 2006-CE-18-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.

Discussion

Mandatory continuing airworthiness information and the FAA's
determination that an unsafe condition existed on a Pilatus Model PC-6
airplane caused us to issue AD 2003-09-01, Amendment 39-13130 (68 FR
22582, April 29, 2003). AD 2003-09-01 currently requires you to inspect
and correct, as necessary, the aileron control bellcrank assemblies at
the wing and fuselage locations on Pilatus Model PC-6 airplanes.
The Federal Office for Civil Aviation (FOCA), which is the
airworthiness authority for Switzerland, notified the FAA of the need
to supersede AD 2003-09-01 to address an unsafe condition that may
exist or could develop on Model PC-6 airplanes, all manufacturer serial
numbers (MSN) up to and including 939. The FOCA reports that the AD
action should also apply to all the models of the PC-6 airplanes listed
in the type certification data sheet of TC No. 7A15 produced in the
United States through a licensing agreement between Pilatus and
Fairchild Republic Company (also identified as Fairchild Industries,
Fairchild Heli Porter, or Fairchild-Hiller Corporation).
This condition, if not corrected, could result in increased
friction in the aileron control bellcrank assemblies, which could
result in failure of the aileron flight-control system. Such failure
could lead to problems in controlling flight.

Foreign Airworthiness Authority Information

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

FAA's Determination and Requirements of the Proposed AD

We are proposing this AD because we have examined the FOCA's
findings, evaluated all information and determined the unsafe condition
described previously is likely to exist or develop on other products of
the same type design that are certificated for operation in the United
States.
This proposed AD would supersede AD 2003-09-01 with a new AD that
would retain all the actions of AD 2003-09-01 and would:
Add manufacturer serial numbers (MSN) 2001 through 2092
for all the models of the PC-6 airplanes as listed in TC No. 7A15 and
specified in the applicability section. These MSN are the airplanes
produced in the United States through a licensing agreement with the
Fairchild Republic Company; and
List all the models of the PC-6 airplanes as listed in TC
No. 7A15.

Costs of Compliance

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

[[Page 26893]]

----------------------------------------------------------------------------------------------------------------
Total cost
Labor cost Parts cost per airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
7 work hours x $80 per hour = $560....... $300 $860 $860 x 49 = $42,140.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

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

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing Airworthiness Directive
(AD) 2003-09-01, Amendment 39-13130, and adding the following new AD:

Pilatus Aircraft LTD.: Docket No. FAA-2006-24092; Directorate
Identifier 2006-CE-18-AD.

Comments Due Date

(a) We must receive comments on this airworthiness directive
(AD) action by June 9, 2006.

Affected ADs

(b) This AD supersedes AD 2003-09-01, Amendment 39-13130.

Applicability

(c) This AD affects the following 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 that are equipped with turbo-prop engines and are
certificated in any category:
(1) Group 1 (maintains the actions from AD 2003-09-01): All
manufacturer serial numbers (MSN) up to and including 939.
(2) Group 2: MSN 2001 through 2092.

Note: These airplanes are also identified as Fairchild Republic
Company PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or
Fairchild-Hiller Corporation PC-6 airplanes.

Unsafe Condition

(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland that requires retaining the actions of AD 2003-09-01 and
adding MSN 2001 through 2092 for all the models of the PC-6
airplanes listed in the type certificate data sheet of Type
Certificate (TC) No. 7A15. We are issuing this AD to detect and
correct increased friction in the aileron control bellcrank
assemblies, which could result in failure of the aileron flight-
control system. Such failure could lead to problems in controlling
flight.

Compliance

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

------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect, before removal (A) For Group 1 Follow Pilatus
of the wing bellcrank Airplanes: Within Aircraft Ltd. PC-6
assemblies, part numbers (P/ the next 100 hours Service Bulletin
N) 6132.0071.51 and time-in-service No. 27-001, dated
6132.0071.52, for installed (TIS) after June June 5, 2002.
circlips, P/N N237: 17, 2003 (the
(i) If circlips are effective date of
installed, do the actions AD 2003-09-01),
required in paragraphs unless already done.
(e)(5) and (e)(6) of this (B) For Group 2
AD. Airplanes: Within
(ii) If circlips are not the next 100 hours
installed, perform all TIS after the
actions required by effective date of
paragraphs (e)(3), (e)(4), this AD, unless
(e)(5), (e)(6), and (e)(7) already done.
of this AD.

[[Page 26894]]

(2) Inspect, before removal Before further Follow Pilatus
of the fuselage bellcrank flight after the Aircraft Ltd. PC-6
assembly, P/N 6232.0118.00, inspection required Service Bulletin
for the circlip installed in paragraph (e)(1) No. 27-001, dated
on the housing to prevent of this AD. June 5, 2002.
axial movement of the
bellcrank on its bearing
and the flange of the
housing to the rear. If the
fuselage bellcrank assembly
has either no circlip and/
or it is not installed as
required, perform the
actions in paragraphs
(e)(8) and (e)(9) of this
AD.
(3) Remove the wing Before further Follow Pilatus
bellcrank assemblies, P/Ns flight after the Aircraft Ltd. PC-6
6132.0071.51 and inspections Service Bulletin
6132.0071.52, and inspect required in No. 27-001, dated
for worn or damaged paragraphs (e)(1) June 5, 2002.
bearings. Replace worn or and (e)(2) of this
damaged bearings. AD, as applicable.
(4) Stake and lock the Before further Follow Pilatus
bearing in the housing of flight after the Aircraft Ltd. PC-6
the wing bellcranks, P/Ns inspections Service Bulletin
6132.0071.51 and required in No. 27-001, dated
6132.0071.52. paragraphs (e)(1) June 5, 2002.
and (e)(2) of this
AD, as applicable.
(5) Inspect the wing Before further Follow Pilatus
bellcranks control-cable flight after the Aircraft Ltd. PC-6
attachment bolts for inspections Service Bulletin
correct type and for signs required in No. 27-001, dated
of rub damage on the heads. paragraphs (e)(1) June 5, 2002.
Replace bolts that are and (e)(2) of this
damaged and/or have a total AD.
length (including head) of
more than 21.5 mm (0.85
in.)
(6) Inspect the wing Before further Follow Pilatus
bellcranks support plate flight after the Aircraft Ltd. PC-6
for signs of rub damage inspections Service Bulletin
caused by the bolts. If required in No. 27-001, dated
damage is found: paragraphs (e)(1) June 5, 2002.
(i) Obtain a repair scheme and (e)(2) of this
from the manufacturer AD.
through FAA at the address
specified in paragraph (f)
of this AD.
(ii) Incorporate this repair
scheme..
(7) Reinstall wing bellcrank Before further Follow Pilatus
assemblies. flight after the Aircraft Ltd. PC-6
inspections Service Bulletin
required in No. 27-001, dated
paragraphs (e)(1) June 5, 2002.
and (e)(2) of this
AD.
(8) Remove the fuselage Before further Follow Pilatus
bellcrank assembly, P/N flight after the Aircraft Ltd. PC-6
6232.0118.00, and inspect inspections Service Bulletin
the housing for wear, required in No. 27-001, dated
damage, and signs of axial paragraphs (e)(1) June 5, 2002.
movement of the bearing in and (e)(2) of this
the housing. Replace worn AD.
or damaged bearings. If any
signs of axial movement of
a bearing are found:
(i) Obtain a repair scheme
from the manufacturer
through FAA at the address
specified in paragraph (f)
of this AD.
(ii) Incorporate this repair
scheme..
(9) Reinstall the fuselage Before further Follow Pilatus
bellcrank assembly. Ensure flight after the Aircraft Ltd. PC-6
that the fuselage bellcrank inspections Service Bulletin
assembly is installed so required in No. 27-001, dated
that the surface of the paragraphs (e)(1), June 5, 2002.
bellcrank with the flange (e)(2) and (e)(8)
of the housing is installed of this AD.
to the rear. The effect of
this is to lock the
bellcrank on the bearing
tube and thus prevent
movement.
(10) Do not install any (A) For Group 1 Follow Pilatus
bellcrank assemblies, P/Ns Airplanes: As of Aircraft Ltd. PC-6
6132.0071.51, 6132,0071.52, June 17, 2003 (the Service Bulletin
and 6232.0118.00 (or FAA- effective date of No. 27-001, dated
approved equivalent part AD 2003-09-01). June 5, 2002.
numbers), unless the (B) For Group 2
aileron assembly has been Airplanes: As of
inspected, modified, and the effective date
installed. of this AD.
------------------------------------------------------------------------

Note 1: Axial movement of serviceable bearings in the housings
of the wing bellcranks is permitted provided no wear or damage to
the bearing is found.

Note 2: Any signs of axial movement of a bearing in the housing
of the fuselage bellcrank assembly requires that you obtain a repair
scheme from the manufacturer through FAA at the address specified in
paragraph (f) of this AD and incorporate the repair scheme.

Alternative Methods of Compliance (AMOCs)

(f) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile:
(816) 329-4090, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 2003-09-01 are approved for this AD.

Related Information

(h) To get copies of the documents referenced in this AD,
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371
Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41
619 6224. To view the AD docket, go to the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC, or on the
Internet at https://dms.dot.gov. The docket number is Docket No. FAA-
2006-24092; Directorate Identifier 2006-CE-18-AD.

Issued in Kansas City, Missouri, on May 3, 2006.
Barry R. Ballenger,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-7017 Filed 5-8-06; 8:45 am]
BILLING CODE 4910-13-P

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