Airworthiness Directives; Erickson Air-Crane Incorporated (Erickson) Model S-64F Helicopters, 71952-71955 [E8-28109]

Download as PDF 71952 Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules 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 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. Would 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. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration 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 adding the following new airworthiness directive: CFM International S.A.: Docket No. FAA– 2008–1245; Directorate Identifier 2008– NE–27–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by January 26, 2009. jlentini on PROD1PC65 with PROPOSALS Applicability (c) This AD applies to CFM International S.A. CFM56–2, CFM56–3, CFM56–5A, CFM56–5B, CFM56–5C, and CFM56–7B series turbofan engines with a high-pressure compressor (HPC) 4–9 spool that has a part number (P/N) and serial number (SN) specified in Table 1 of this AD, installed. 17:02 Nov 25, 2008 Jkt 217001 TABLE 1—HPC 4–9 SPOOLS BY P/N AND SN HPC 4–9 Spool P/N 9513M93G08 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1590M29G01 1588M89G03 1588M89G03 1588M89G03 1588M89G03 1588M89G03 1588M89G03 1277M97G02 1277M97G02 1277M97G02 1277M97G02 9513M93G11 1358M94G01 ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ ............ HPC 4–9 Spool SN MPON1641 GWN0087D GWN00MG2 GWN011LG GWN01285 GWN021JC GWNFY923 GWNFY824 GWNPA756 GWNPG015 GWNWC515 GWNWR523 GWNWT631 GWNYC495 GWN03K1R GWN03N61 GWN03N6C GWN040L9 GWN0468N GWN05AMO GWNE1298 GWNE1564 GWNJ7891 GWNT4187 GWNB3373 GWNU0169 Unsafe Condition (d) This AD results from reports of certain HPC 4–9 spools that Propulsion Technology LLC (PTLLC) improperly repaired and returned to service. We are issuing this AD to prevent cracking of the HPC 4–9 spool, which could result in possible uncontained failure of the spool and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Removing the HPC 4–9 Spool (f) Remove HPC 4–9 spools from service that have a P/N and S/N listed in Table 1 of this AD before accumulating 8,900 cycles since repair at PTLLC or within 1,100 cycles from the effective date of this AD, whichever occurs later. Installation Prohibition (g) After the effective date of this AD, do not install any engine with an HPC 4–9 spool that has a P/N and SN specified in Table 1 of this AD. Affected ADs (b) None. VerDate Aug<31>2005 These engines are installed on, but not limited to, Airbus A319, A320, and A340 airplanes and Boeing 737 airplanes. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (i) Contact Stephen K. Sheely, Aerospace Engineer, Engine Certification Office, FAA, PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: stephen.k.sheely@faa.gov; telephone (781) 238–7750; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on November 18, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–28055 Filed 11–25–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1243; Directorate Identifier 2007–SW–03–AD] RIN 2120–AA64 Airworthiness Directives; Erickson AirCrane Incorporated (Erickson) Model S–64F Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for Erickson Model S–64F helicopters. The AD would require inspections for cracking or working rivets in each left and right splice fitting (transition fitting), the pylon bulkhead assembly—canted (bulkhead assembly), the pylon steel strap (strap), and the attaching rotary rudder boom and pylon structure. This proposal is prompted by several reports of cracking in the transition fittings, the bulkhead assembly, and pylon. The actions specified by the proposed AD are intended to detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter. DATES: Comments must be received on or before January 26, 2009. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– E:\FR\FM\26NOP1.SGM 26NOP1 Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow Springs Rd., PO Box 3247, Central Point, OR 97502, telephone (541) 664–5544, fax (541) 664–2312, email address cerickson@ericksonaircrane.com. FOR FURTHER INFORMATION CONTACT: jlentini on PROD1PC65 with PROPOSALS Michael Kohner, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, Fort Worth, Texas 76193–0170, telephone (817) 222–5170, fax (817) 222–5783. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2008–1243, Directorate Identifier 2007–SW–03–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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477). Examining the Docket: You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647– 5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. VerDate Aug<31>2005 17:02 Nov 25, 2008 Jkt 217001 Discussion This document proposes adopting a new AD for Erickson Model S–64F helicopters with a transition fitting, part number (P/N) 6420–66341–101, –102, –103, or –104, a bulkhead assembly, P/ N 6420–66340–041, –043, or –044, or a strap, P/N 6420–66301–119 or –127, installed. The AD would require inspections for cracking or working rivets in each transition fitting, the bulkhead assembly, the strap, and the attaching rotary rudder boom and pylon structure, and replacing or repairing any cracked or damaged part with an airworthy part. This proposal is prompted by several reports of cracking in the transition fittings, the bulkhead assembly, and the pylon. The cracks were discovered during inspections. The actions specified by the proposed AD are intended to detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter. We have reviewed Erickson Service Bulletin (SB) No. 64B20–6, Revision A, dated December 12, 2007, which describes procedures for inspecting the transition fittings, the bulkhead assembly, the strap, and the attaching rotary rudder boom and pylon structure for cracking or working rivets. We have also reviewed Erickson SB No. 64F General–3, Revision C, dated December 12, 2007, which summarizes a listing of a portion of the Model S–64F helicopter components, their part numbers, and the corresponding service bulletins to use when performing the structural inspections. The unsafe condition associated with the fatigue cracking and working rivets is likely to exist or develop on other helicopters of the same type design. Therefore, the proposed AD would require, within 20 hours time-in-service (TIS), and thereafter at intervals not to exceed 20 hours TIS: • Visually inspecting each transition fitting for a crack or working rivets on the inboard face of the rotary rudder boom and pylon; • Visually inspecting the outboard face of each rotary rudder boom and pylon skin panel (skin panel) that attaches to the transition fittings for a crack or working rivets in the transition fitting attachment areas; • Visually inspecting the forward and aft sides of the bulkhead assembly for a crack; • Visually inspecting the upper 12 inches of the strap for a crack or for working rivets; and • Visually inspecting the pylon on each side of the upper 12 inches of the PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 71953 strap, and also 6 inches above the strap, for a crack or working rivets. For any pylon with a strap installed, the proposed AD would require, within 155 hours TIS, and thereafter at intervals not to exceed 155 hours TIS, removing the inspection panels, P/N 6420–66304–109 and 6420–66303–125, on the forward and aft sides of the pylon, and visually inspecting the lefthand cap angle (longeron), P/N 6420– 66304–136, and the interior area of the pylon that is adjacent to the upper 12 inches of the strap, as well as 6 inches above the end of the strap, for a crack or working rivets. At each 8,300 hours TIS transition fitting replacement, the proposed AD would require: • With the transition fitting removed, visually inspecting both sides of each skin panel for a crack in the areas to which the transition fitting attaches; and • Performing a fluorescent penetrant inspection of the skin panels for a crack in the area around the fastener holes attaching the transition fittings to the rotary rudder boom and pylon. The proposed AD would also require, before further flight: • Inspecting any part and the surrounding area using a 10-power or higher magnifying glass if you cannot visually determine that a crack does not exist in that part; • Performing a fluorescent penetrant inspection of any part, other than a strap, if you cannot determine that a crack does not exist in the part after inspecting it with a 10-power or higher magnifying glass; • Performing a magnetic particle inspection of any strap if you cannot determine that a crack does not exist in the strap after inspecting it with a 10power or higher magnifying glass; • If a crack is found, replacing any cracked part with an airworthy part or repairing that part if it is within the maximum repair damage limits; and • If any loose or working rivets are found, removing the rivets, visually inspecting the fastener holes and surrounding area for a crack or any other damage, and replacing any cracked part with an airworthy part or replacing any damaged part with an airworthy part if the damage exceeds the maximum repair damage limits or repairing any damaged part, if the part is within the maximum repair damage limits. Finally, replacing any loose or working rivet would be required. The actions would be required to be accomplished by following specified portions of the service bulletin described previously. We estimate that this proposed AD would affect 7 helicopters of U.S. E:\FR\FM\26NOP1.SGM 26NOP1 71954 Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules registry, and the proposed actions would take approximately: • 0.75 work hour for the visual inspection of the transition fittings, skin panels, the bulkhead assembly, strap, and pylon exterior in the strap area with 30 inspections per year; • 0.50 work hour for the visual inspection of the pylon interior in the strap area with 4 inspections per year; • 0.75 work hour for the visual and fluorescent penetrant inspections of the skin panels at the transition fitting with 1 inspection per year; and • 40 work hours per helicopter to repair a pylon structural assembly. The average labor rate is $80 per work hour. Required parts would cost approximately $50,000 per helicopter to repair a pylon structural assembly, if needed. The estimated cost of labor for the inspections of 7 helicopters would be $14,140. The estimated cost to repair the pylon structural assembly on a helicopter, including the cost of the replacement parts and labor, would be $53,200. Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $67,340 per year for the fleet, assuming a pylon structural assembly on one helicopter would need to be repaired. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, 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 an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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. 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 PART 39—AIRWORTHINESS DIRECTIVES List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Erickson Air-Crane Incorporated: Docket No. FAA–2008–1243; Directorate Identifier 2007–SW–03–AD. Applicability: Model S–64F helicopters, with any of the parts listed in Table 1 of this AD installed, certificated in any category. TABLE 1 Installed part Part number (P/N) jlentini on PROD1PC65 with PROPOSALS Left or right splice fitting (transition fitting) ................................................................................. Pylon bulkhead assembly—canted (bulkhead assembly) .......................................................... Pylon steel strap (strap) ............................................................................................................. Compliance: Required as indicated. To detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter, accomplish the following: (a) Within 20 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 20 hours TIS: (1) Visually inspect each transition fitting, P/N 6420–66341–101, –102, –103, or –104, for a crack or working rivets on the inboard face of the rotary rudder boom and pylon, paying particular attention to the fastener attachment holes, as depicted in Figure 1, Detail A, of the Accomplishment Instructions in Erickson Air-Crane Incorporated Service Bulletin No. 64B20–6, Revision A, dated December 12, 2007 (SB). (2) Visually inspect the outboard face of each rotary rudder boom and pylon skin panel (skin panel) that attaches to the VerDate Aug<31>2005 17:02 Nov 25, 2008 Jkt 217001 6420–66341–101, –102, –103, or –104 6420–66340–041, –043, or –044 6420–66301–119 or –127 transition fittings for a crack or working rivets in the transition fitting attachment areas, paying particular attention to the fastener attachment holes, as shown in Figure 1, Detail B, of the Accomplishment Instructions in the SB. (3) Visually inspect the forward and aft sides of each bulkhead assembly, P/N 6420– 66340–041, –043, or –044, for a crack. Pay particular attention to the circled areas shown in Figure 2 of the Accomplishment Instructions in the SB. (4) Visually inspect the upper 12 inches of each strap, P/N 6420–66301–119 or –127, for a crack or for working rivets as shown in Figure 3 of the Accomplishment Instructions in the SB. (5) Visually inspect the pylon for a crack or working rivets on each side of the upper 12 inches of the strap, and also 6 inches above the end of the strap as shown in Figure 3 of the Accomplishment Instructions in the SB. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (b) For any pylon with a strap installed, within 155 hours TIS, unless previously accomplished, and thereafter at intervals not to exceed 155 hours TIS, remove the inspection access covers, P/N 6420–66304– 109 and P/N 6420–66303–125, on the forward and aft sides of the pylon and visually inspect the left-hand cap angle (longeron), P/N 6420–66304–136, and the interior area of the pylon adjacent to the upper 12 inches of the strap, as well as 6 inches above the end of the strap, for a crack or working rivets, as shown in Figure 3 of the Accomplishment Instructions in the SB. (c) At each transition fitting replacement, which is required at intervals not to exceed 8,300 hours TIS: (1) With each transition fitting removed, visually inspect both sides of each skin panel for a crack in the areas to which the transition fitting attaches, paying particular attention to the fastener attachment holes, as E:\FR\FM\26NOP1.SGM 26NOP1 Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules jlentini on PROD1PC65 with PROPOSALS depicted in Details A and B, Figure 1, of the Accomplishment Instructions in the SB. (2) Perform a fluorescent penetrant inspection of each skin panel for a crack in the areas around the fastener holes where the transition fittings attach to the rotary rudder boom and pylon. (d) Before further flight, accomplish the following: (1) If you cannot visually determine that a crack does not exist in a part, inspect the part and the surrounding area using a 10-power or higher magnifying glass. (2) If you cannot determine that a crack does not exist in a part other than a strap after inspecting it with a 10-power or higher magnifying glass, perform a fluorescent penetrant inspection of the part. (3) If you cannot determine that a crack does not exist in a strap after inspecting it with a 10-power or higher magnifying glass, perform a magnetic particle inspection of the strap. (e) If a crack is found, before further flight, replace any cracked part with an airworthy part, or repair the cracked part if the damage is within the maximum repair damage limits. Note: The maximum repair damage limitations are stated in the applicable Component and Repair Overhaul Manual. (f) If any loose or working rivets are found, before further flight, remove the rivets and visually inspect the fastener holes and surrounding area for a crack or any other damage. Replace any part that is cracked with an airworthy part; replace any damaged part with damage exceeding the maximum repair damage limits with an airworthy part or repair any damaged part that is within the maximum repair damage limits. Also, replace any loose or working rivets. (g) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Rotorcraft Certification Office, FAA, ATTN: Michael Kohner, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, Fort Worth, Texas 76193–0170, telephone (817) 222–5170, fax (817) 222– 5783, for information about previously approved alternative methods of compliance. (h) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the inspection requirements of this AD can be accomplished. No special flight permits will be issued to accomplish replacements or repairs, or if a crack is suspected. Issued in Fort Worth, Texas, on November 14, 2008. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–28109 Filed 11–25–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 17:02 Nov 25, 2008 Jkt 217001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1242; Directorate Identifier 96–SW–13–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Model 206L, 206L–1, and 206L–3 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes to revise an existing airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206L, 206L–1, and 206L–3 helicopters with certain part-numbered tailbooms. That AD currently requires a visual inspection of the tailboom skin in the areas around the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion using a 10-power or higher magnifying glass until the tailboom is replaced with an airworthy tailboom. This action would require the same actions as the existing AD but would allow a longer interval for the repetitive inspections if the tailboom is modified. Replacement with an airworthy tailboom other than a part-numbered tailboom affected by this proposal would constitute terminating action for the requirements of this AD. The existing AD was prompted by an accident and several reports of fatigue cracks in the tailboom skin in the areas around the nutplates for the tail rotor fairing and in the areas of the tail rotor drive shaft cover retention clips. These proposed actions are intended to prevent failure of the tailboom and subsequent loss of control of the helicopter. DATES: Comments must be received by January 26, 2009. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 71955 Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272, or at http:// www.bellcustomer.com/files/. Examining the Docket: You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647– 5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2008–1242, Directorate Identifier 96–SW–13–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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Discussion On August 22, 1996, we issued AD 96–18–05, Amendment 39–9729 (61 FR E:\FR\FM\26NOP1.SGM 26NOP1

Agencies

[Federal Register Volume 73, Number 229 (Wednesday, November 26, 2008)]
[Proposed Rules]
[Pages 71952-71955]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28109]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1243; Directorate Identifier 2007-SW-03-AD]
RIN 2120-AA64


Airworthiness Directives; Erickson Air-Crane Incorporated 
(Erickson) Model S-64F Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Erickson Model S-64F helicopters. The AD would require 
inspections for cracking or working rivets in each left and right 
splice fitting (transition fitting), the pylon bulkhead assembly--
canted (bulkhead assembly), the pylon steel strap (strap), and the 
attaching rotary rudder boom and pylon structure. This proposal is 
prompted by several reports of cracking in the transition fittings, the 
bulkhead assembly, and pylon. The actions specified by the proposed AD 
are intended to detect cracking in the rotary rudder boom or pylon due 
to fatigue, and to prevent failure from static overload and subsequent 
loss of control of the helicopter.

DATES: Comments must be received on or before January 26, 2009.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-

[[Page 71953]]

30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, 
SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
from Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance 
Officer, 3100 Willow Springs Rd., PO Box 3247, Central Point, OR 97502, 
telephone (541) 664-5544, fax (541) 664-2312, e-mail address 
cerickson@ericksonaircrane.com.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5170, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2008-1243, 
Directorate Identifier 2007-SW-03-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 http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed rulemaking. Using the 
search function of our docket web site, you can find and read the 
comments to any of our dockets, including the name of the individual 
who sent or signed the comment. You may review the DOT's complete 
Privacy Act Statement in the Federal Register published on April 11, 
2000 (65 FR 19477).
    Examining the Docket: You may examine the docket that contains the 
proposed AD, any comments, and other information in person at the 
Docket Operations office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Operations office 
(telephone (800) 647-5527) is located in Room W12-140 on the ground 
floor of the West Building at the street address stated in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

Discussion

    This document proposes adopting a new AD for Erickson Model S-64F 
helicopters with a transition fitting, part number (P/N) 6420-66341-
101, -102, -103, or -104, a bulkhead assembly, P/N 6420-66340-041, -
043, or -044, or a strap, P/N 6420-66301-119 or -127, installed. The AD 
would require inspections for cracking or working rivets in each 
transition fitting, the bulkhead assembly, the strap, and the attaching 
rotary rudder boom and pylon structure, and replacing or repairing any 
cracked or damaged part with an airworthy part. This proposal is 
prompted by several reports of cracking in the transition fittings, the 
bulkhead assembly, and the pylon. The cracks were discovered during 
inspections. The actions specified by the proposed AD are intended to 
detect cracking in the rotary rudder boom or pylon due to fatigue, and 
to prevent failure from static overload and subsequent loss of control 
of the helicopter.
    We have reviewed Erickson Service Bulletin (SB) No. 64B20-6, 
Revision A, dated December 12, 2007, which describes procedures for 
inspecting the transition fittings, the bulkhead assembly, the strap, 
and the attaching rotary rudder boom and pylon structure for cracking 
or working rivets. We have also reviewed Erickson SB No. 64F General-3, 
Revision C, dated December 12, 2007, which summarizes a listing of a 
portion of the Model S-64F helicopter components, their part numbers, 
and the corresponding service bulletins to use when performing the 
structural inspections.
    The unsafe condition associated with the fatigue cracking and 
working rivets is likely to exist or develop on other helicopters of 
the same type design. Therefore, the proposed AD would require, within 
20 hours time-in-service (TIS), and thereafter at intervals not to 
exceed 20 hours TIS:
     Visually inspecting each transition fitting for a crack or 
working rivets on the inboard face of the rotary rudder boom and pylon;
     Visually inspecting the outboard face of each rotary 
rudder boom and pylon skin panel (skin panel) that attaches to the 
transition fittings for a crack or working rivets in the transition 
fitting attachment areas;
     Visually inspecting the forward and aft sides of the 
bulkhead assembly for a crack;
     Visually inspecting the upper 12 inches of the strap for a 
crack or for working rivets; and
     Visually inspecting the pylon on each side of the upper 12 
inches of the strap, and also 6 inches above the strap, for a crack or 
working rivets.
    For any pylon with a strap installed, the proposed AD would 
require, within 155 hours TIS, and thereafter at intervals not to 
exceed 155 hours TIS, removing the inspection panels, P/N 6420-66304-
109 and 6420-66303-125, on the forward and aft sides of the pylon, and 
visually inspecting the left-hand cap angle (longeron), P/N 6420-66304-
136, and the interior area of the pylon that is adjacent to the upper 
12 inches of the strap, as well as 6 inches above the end of the strap, 
for a crack or working rivets. At each 8,300 hours TIS transition 
fitting replacement, the proposed AD would require:
     With the transition fitting removed, visually inspecting 
both sides of each skin panel for a crack in the areas to which the 
transition fitting attaches; and
     Performing a fluorescent penetrant inspection of the skin 
panels for a crack in the area around the fastener holes attaching the 
transition fittings to the rotary rudder boom and pylon.
    The proposed AD would also require, before further flight:
     Inspecting any part and the surrounding area using a 10-
power or higher magnifying glass if you cannot visually determine that 
a crack does not exist in that part;
     Performing a fluorescent penetrant inspection of any part, 
other than a strap, if you cannot determine that a crack does not exist 
in the part after inspecting it with a 10-power or higher magnifying 
glass;
     Performing a magnetic particle inspection of any strap if 
you cannot determine that a crack does not exist in the strap after 
inspecting it with a 10-power or higher magnifying glass;
     If a crack is found, replacing any cracked part with an 
airworthy part or repairing that part if it is within the maximum 
repair damage limits; and
     If any loose or working rivets are found, removing the 
rivets, visually inspecting the fastener holes and surrounding area for 
a crack or any other damage, and replacing any cracked part with an 
airworthy part or replacing any damaged part with an airworthy part if 
the damage exceeds the maximum repair damage limits or repairing any 
damaged part, if the part is within the maximum repair damage limits.
    Finally, replacing any loose or working rivet would be required. 
The actions would be required to be accomplished by following specified 
portions of the service bulletin described previously.
    We estimate that this proposed AD would affect 7 helicopters of 
U.S.

[[Page 71954]]

registry, and the proposed actions would take approximately:
     0.75 work hour for the visual inspection of the transition 
fittings, skin panels, the bulkhead assembly, strap, and pylon exterior 
in the strap area with 30 inspections per year;
     0.50 work hour for the visual inspection of the pylon 
interior in the strap area with 4 inspections per year;
     0.75 work hour for the visual and fluorescent penetrant 
inspections of the skin panels at the transition fitting with 1 
inspection per year; and
     40 work hours per helicopter to repair a pylon structural 
assembly.
    The average labor rate is $80 per work hour. Required parts would 
cost approximately $50,000 per helicopter to repair a pylon structural 
assembly, if needed. The estimated cost of labor for the inspections of 
7 helicopters would be $14,140. The estimated cost to repair the pylon 
structural assembly on a helicopter, including the cost of the 
replacement parts and labor, would be $53,200. Based on these figures, 
the total cost impact of the proposed AD on U.S. operators is estimated 
to be $67,340 per year for the fleet, assuming a pylon structural 
assembly on one helicopter would need to be repaired.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, 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 an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Erickson Air-Crane Incorporated: Docket No. FAA-2008-1243; 
Directorate Identifier 2007-SW-03-AD.

    Applicability: Model S-64F helicopters, with any of the parts 
listed in Table 1 of this AD installed, certificated in any 
category.

                                                     Table 1
----------------------------------------------------------------------------------------------------------------
             Installed part                                         Part number (P/N)
----------------------------------------------------------------------------------------------------------------
Left or right splice fitting             6420-66341-101, -102, -103, or -104
 (transition fitting).
Pylon bulkhead assembly--canted          6420-66340-041, -043, or -044
 (bulkhead assembly).
Pylon steel strap (strap)..............  6420-66301-119 or -127
----------------------------------------------------------------------------------------------------------------

    Compliance: Required as indicated.
    To detect cracking in the rotary rudder boom or pylon due to 
fatigue, and to prevent failure from static overload and subsequent 
loss of control of the helicopter, accomplish the following:
    (a) Within 20 hours time-in-service (TIS), unless accomplished 
previously, and thereafter at intervals not to exceed 20 hours TIS:
    (1) Visually inspect each transition fitting, P/N 6420-66341-
101, -102, -103, or -104, for a crack or working rivets on the 
inboard face of the rotary rudder boom and pylon, paying particular 
attention to the fastener attachment holes, as depicted in Figure 1, 
Detail A, of the Accomplishment Instructions in Erickson Air-Crane 
Incorporated Service Bulletin No. 64B20-6, Revision A, dated 
December 12, 2007 (SB).
    (2) Visually inspect the outboard face of each rotary rudder 
boom and pylon skin panel (skin panel) that attaches to the 
transition fittings for a crack or working rivets in the transition 
fitting attachment areas, paying particular attention to the 
fastener attachment holes, as shown in Figure 1, Detail B, of the 
Accomplishment Instructions in the SB.
    (3) Visually inspect the forward and aft sides of each bulkhead 
assembly, P/N 6420-66340-041, -043, or -044, for a crack. Pay 
particular attention to the circled areas shown in Figure 2 of the 
Accomplishment Instructions in the SB.
    (4) Visually inspect the upper 12 inches of each strap, P/N 
6420-66301-119 or -127, for a crack or for working rivets as shown 
in Figure 3 of the Accomplishment Instructions in the SB.
    (5) Visually inspect the pylon for a crack or working rivets on 
each side of the upper 12 inches of the strap, and also 6 inches 
above the end of the strap as shown in Figure 3 of the 
Accomplishment Instructions in the SB.
    (b) For any pylon with a strap installed, within 155 hours TIS, 
unless previously accomplished, and thereafter at intervals not to 
exceed 155 hours TIS, remove the inspection access covers, P/N 6420-
66304-109 and P/N 6420-66303-125, on the forward and aft sides of 
the pylon and visually inspect the left-hand cap angle (longeron), 
P/N 6420-66304-136, and the interior area of the pylon adjacent to 
the upper 12 inches of the strap, as well as 6 inches above the end 
of the strap, for a crack or working rivets, as shown in Figure 3 of 
the Accomplishment Instructions in the SB.
    (c) At each transition fitting replacement, which is required at 
intervals not to exceed 8,300 hours TIS:
    (1) With each transition fitting removed, visually inspect both 
sides of each skin panel for a crack in the areas to which the 
transition fitting attaches, paying particular attention to the 
fastener attachment holes, as

[[Page 71955]]

depicted in Details A and B, Figure 1, of the Accomplishment 
Instructions in the SB.
    (2) Perform a fluorescent penetrant inspection of each skin 
panel for a crack in the areas around the fastener holes where the 
transition fittings attach to the rotary rudder boom and pylon.
    (d) Before further flight, accomplish the following:
    (1) If you cannot visually determine that a crack does not exist 
in a part, inspect the part and the surrounding area using a 10-
power or higher magnifying glass.
    (2) If you cannot determine that a crack does not exist in a 
part other than a strap after inspecting it with a 10-power or 
higher magnifying glass, perform a fluorescent penetrant inspection 
of the part.
    (3) If you cannot determine that a crack does not exist in a 
strap after inspecting it with a 10-power or higher magnifying 
glass, perform a magnetic particle inspection of the strap.
    (e) If a crack is found, before further flight, replace any 
cracked part with an airworthy part, or repair the cracked part if 
the damage is within the maximum repair damage limits.

    Note: The maximum repair damage limitations are stated in the 
applicable Component and Repair Overhaul Manual.

    (f) If any loose or working rivets are found, before further 
flight, remove the rivets and visually inspect the fastener holes 
and surrounding area for a crack or any other damage. Replace any 
part that is cracked with an airworthy part; replace any damaged 
part with damage exceeding the maximum repair damage limits with an 
airworthy part or repair any damaged part that is within the maximum 
repair damage limits. Also, replace any loose or working rivets.
    (g) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Rotorcraft Certification Office, FAA, ATTN: 
Michael Kohner, Aviation Safety Engineer, FAA, Rotorcraft 
Directorate, Rotorcraft Certification Office, Fort Worth, Texas 
76193-0170, telephone (817) 222-5170, fax (817) 222-5783, for 
information about previously approved alternative methods of 
compliance.
    (h) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the inspection requirements of this AD can be accomplished. No 
special flight permits will be issued to accomplish replacements or 
repairs, or if a crack is suspected.

    Issued in Fort Worth, Texas, on November 14, 2008.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-28109 Filed 11-25-08; 8:45 am]
BILLING CODE 4910-13-P