Airworthiness Directives; Bell Helicopter Textron Canada Model 222, 222B, 222U, 230, and 430 Helicopters, 43648-43652 [E8-17261]

Download as PDF 43648 Federal Register / Vol. 73, No. 145 / Monday, July 28, 2008 / Proposed Rules gross weight necessary, (2) the manufacturer covers all the costs of the parts and the labor costs associated with the rigging adjustment and installation of the thruster extension kit and (3) only 3 helicopters need to have a new fan felt seal installed. Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: Regulatory Findings 1. The authority citation for part 39 continues to read as follows: 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 a draft economic evaluation of the estimated costs to comply with this proposed AD. See the AD docket to examine the draft economic evaluation. Authority for This Rulemaking yshivers on PROD1PC66 with PROPOSALS 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, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the VerDate Aug<31>2005 15:00 Jul 25, 2008 Jkt 214001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 PART 39—AIRWORTHINESS DIRECTIVES [Docket No. FAA–2008–0071; Directorate Identifier 2006–SW–27–AD] 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: MD Helicopters, Inc.: Docket No. FAA–2008– 0772; Directorate Identifier 2008–SW– 30–AD. Applicability: Model MD900 (including MD902 Configuration) helicopters that have not complied with MD Helicopters, Inc. (MDHI) Service Bulletin SB900–099 R1, dated December 27, 2006, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of directional control of the helicopter, accomplish the following: (a) Within 30 days, reduce the gross weight limit to a maximum gross weight limit of 5,400 pounds by inserting a copy of this AD into the Limitations section of the RFM. (b) As an optional terminating action for the weight reduction mandated by paragraph (a) of this AD, accomplish the following: (1) Determine if a NOTAR fan felt seal part number (P/N) 900F3441025–103 is installed. If a NOTAR fan felt seal, P/N 900F3441025– 103, is not installed, replace the installed seal with an airworthy NOTAR fan felt seal, P/N 900F3441025–103, before further flight. (2) Install a thruster extension kit in accordance with the Accomplishment Instructions, paragraph B. (3). through (17). of MDHI SB900–099 R1, dated December 27, 2006 (SB), before further flight. Contacting the manufacturer is not required by this AD. (c) 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, Los Angeles Aircraft Certification Office, Attn: Chip Adam, Flight Test Pilot, FAA, Flight Test Branch, 3960 Paramount Blvd., Lakewood, California 90712–4137, telephone (562) 627– 5369, fax (562) 627–5210, for information about previously approved alternative methods of compliance. (d) Special flight permits will not be issued. Issued in Fort Worth, Texas, on July 8, 2008. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–17262 Filed 7–25–08; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Model 222, 222B, 222U, 230, and 430 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes superseding an existing airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) helicopters. That AD currently requires certain checks and inspections of the tail rotor blades. If a crack is found, the existing AD requires replacing the tail rotor blade (blade) with an airworthy blade before further flight. This action would require the same checks and inspections until they are required to be replaced and would remove certain serial numbered and specifically coded tail rotor blades from the applicability of the AD. This proposal is prompted by the approved rework of certain tail rotor blades and two newly redesigned tail rotor blades, which, if installed, constitutes terminating action for the inspection requirements. The actions specified by the proposed AD are intended to detect a crack in a blade, and to prevent loss of a blade and subsequent loss of control of the helicopter. Comments must be received on or before September 26, 2008. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to https://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., 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 DATES: E:\FR\FM\28JYP1.SGM 28JYP1 Federal Register / Vol. 73, No. 145 / Monday, July 28, 2008 / Proposed Rules de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272. You may examine the comments to this proposed AD in the AD docket on the Internet at https:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy 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–2008–0071, Directorate Identifier 2006–SW–27–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:// 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 the 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 19477–19478). yshivers on PROD1PC66 with PROPOSALS Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 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 On February 10, 2005, we issued AD 2005–04–09, Amendment 39–13981 (70 FR 8021, February 17, 2005), that VerDate Aug<31>2005 15:00 Jul 25, 2008 Jkt 214001 superseded AD 2004–26–11, Amendment 39–13923 (70 FR 7, January 3, 2005), to require the following: • Within 3 hours time-in-service (TIS), and thereafter at intervals not to exceed 3 hours TIS, clean and visually check both sides of each blade for a crack in the area around the tail rotor feathering bearing. An owner/operator (pilot) may perform this check. Pilots may perform the checks required by paragraph (a) of this AD because they require no tools, can be done by observation, and can be done equally well by a pilot or a mechanic. However, the pilot must enter compliance with these requirements into the helicopter maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v). • Within 50 hours TIS, and thereafter at intervals not to exceed 50 hours TIS, clean and inspect both sides of each blade for a crack using a 10X or higher magnifying glass. • If a crack is found in the blade paint during a visual check or inspection, further inspect the blade as follows, before further flight: • Remove the blade. Remove the paint to the bare metal in the area of the suspected crack by using plastic metal blasting (PMB) or a nylon web abrasive pad and abrading the blade surface in a span-wise direction only. (The AD incorrectly used the word ‘‘metal’’ instead of ‘‘media’’.) • Using a 10X or higher power magnifying glass, inspect the blade for a crack. • If a crack is found, replace the blade with an airworthy blade before further flight. • If no crack is found in the blade surface, refinish the blade by applying one coat of epoxy polyamide primer, MIL–P–23377 or MIL–P–85582, so that the primer overlaps the existing coats just beyond the abraded area. Let the area dry for 30 minutes to 1 hour. Then, apply one sealer coat of polyurethane, MILC85285 TYI CL2, color number 27925 (semi-gloss white), per Fed. Std. 595, and reinstall the blade. That action was prompted by reports of cracked blades that were found during scheduled inspections. The requirements of that AD are intended to detect a crack in a blade, and to prevent loss of a blade and subsequent loss of control of the helicopter. AD 2005–04–09 required the same checks and inspections as AD 2004–26– 11, but also expands the applicability of AD 2004–26–11 to include two additional helicopter serial numbers. Since issuing AD 2005–04–09, BHTC has introduced a rework procedure for the affected tail rotor blades and two new part numbered tail rotor blades that PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 43649 eliminates the need for the recurring checks and inspections. Transport Canada, the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on the specified BHTC model helicopters. Transport Canada advises of the discovery of cracked blades during scheduled inspections on three occasions. Two cracks originated from the outboard feathering bearing bore underneath the flanged sleeves. The third crack started from the inboard feathering bearing bore. Investigation found that the cracks originated from either a machining burr or a corrosion site in the bearing bore underneath the flanged sleeves. BHTC has issued Alert Service Bulletin (ASB) No. 222–04–100, Revision B, for Model 222 and 222B helicopters; ASB No. 222U–04–71, Revision B, for Model 222U helicopters; ASB No. 230–04–31, Revision B, for Model 230 helicopters; and ASB No. 430–04–31, Revision C, for Model 430 helicopters, all dated March 31, 2008. The ASBs specify a visual inspection of the blade root end around the feathering bearings for a crack, not later than at the next scheduled inspection, and thereafter at every 3 flight hours maximum. Further, they describe a visual inspection for a crack, to include removing the blade from the helicopter if a crack is found in the paint, within the next 50 flight hours, and thereafter at every 50 flight hours. In addition, the ASBs state that, on or before December 31, 2008, each blade should be reworked by Rotor Blades, Inc., or exchanged if the blade has less than 4,000 hours TIS or if the blade has 4,000 or more hours TIS, the blade should continue to be repetitively inspected or a replacement blade should be ordered. Transport Canada classified these ASBs as mandatory and issued AD CF–2004– 21R3, dated April 23, 2008, to ensure the continued airworthiness of these helicopters in Canada. This proposal differs from the ASB in that it would require, on or before 90 days after the effective date of the AD, replacing all affected tail rotor blades with airworthy tail rotor blades that are not subject to the proposed inspection requirements, without differentiating between blades based on hours TIS. Additionally, operators are not required to send their tail rotor blade to Rotor Blades, Inc. for rework. These helicopter models are manufactured in Canada and are type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, Transport Canada E:\FR\FM\28JYP1.SGM 28JYP1 43650 Federal Register / Vol. 73, No. 145 / Monday, July 28, 2008 / Proposed Rules has kept the FAA informed of the situation described above. The FAA has examined the findings of Transport Canada, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type designs. Therefore, the proposed AD would supersede AD 2005–04–09, and would apply as follows: Helicopter model Helicopter serial No. (S/N) Blade part No. (P/N) 222 .................................................. 47006 through 47089 .................... 222B ................................................ 47131 through 47156 .................... 222U ................................................ 47501 through 47574 .................... 230 .................................................. 23001 through 23038 .................... 430 .................................................. 49001 through 49107 .................... 222–016–001–123, –123M, –127, –127M, –131, –135, –139M, –141M, except those P/Ns with S/Ns listed in Exceptions 1 and 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –127, –127M, –131, –135, –139M, –141M, except those P/Ns with S/Ns listed in Exceptions 1 and 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 2 or the ‘‘R’’ code described in Exception 3. Exception 1: Blade, P/N 222–016– 001–135 or –141M, S/N A–1502, A– 1503, A–1504, A–1505, A–1507, A– 1508, A–1509, A–1510, A–1556, A– 1557, A–1558, A–1560, A–1561, A– 1574, A–1635, A–1636, A–1828, A– 1829, and S/Ns with a prefix of ‘‘A’’ and a number greater than 1829 have the intent of this proposal accomplished prior to delivery and no further action is required by this proposed AD. Exception 2: Blade, P/N 222–016– 001–131 and –139M, S/N A–2049, A– 2055, A–2060, A–2070, A–2071, A– 2085, and S/Ns with a prefix of ‘‘A’’ and a number greater than 2085 have the intent of this proposal accomplished prior to delivery and no further action is required by this proposed AD. Exception 3: Blades identified with an ‘‘R’’ code in the square block below the P/N field of the Data Plate have already been modified and no further actions are required by this proposed AD. yshivers on PROD1PC66 with PROPOSALS Note 1: New blades, P/N 222–016–001–139 and –141, with no letter on the Data Plate after the P/N, are not subject to the requirements of this proposed AD. The proposed AD would require the following: • Within 3 hours TIS, unless accomplished previously, and thereafter at intervals not to exceed 3 hours TIS, clean and visually check both sides of each blade for a crack in the area around the tail rotor feathering bearing. An owner/operator (pilot) holding at least a private pilot certificate may perform this check. Pilots may perform the checks required by paragraph (a) of this proposed AD because they require no tools, can be done by observation, and can be done equally well by a pilot or a mechanic. However, the pilot must enter compliance with these requirements into the helicopter VerDate Aug<31>2005 15:00 Jul 25, 2008 Jkt 214001 maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v). • Within 50 hours TIS, and thereafter at intervals not to exceed 50 hours TIS, clean and inspect both sides of each blade for a crack using a 10X or higher magnifying glass. • If a crack is found in the blade paint during a visual check or inspection, further inspect the blade as follows, before further flight: • Remove the blade. Remove the paint to the bare metal in the area of the suspected crack by using plastic media blasting (PMB) or a nylon web abrasive pad and abrading the blade surface in a span-wise direction only. • Using a 10X or higher power magnifying glass, inspect the blade for a crack. • If a crack is found, replace the blade with an airworthy blade before further flight. • If no crack is found in the blade surface, refinish the blade by applying one coat of epoxy polyamide primer, MIL–P–23377 or MIL–P–85582, so that the primer overlaps the existing coats just beyond the abraded area. Let the area dry for 30 minutes to 1 hour. Then, apply one sealer coat of polyurethane, MILC85285 TYI CL2, color number 27925 (semi-gloss white), per Fed. Std. 595, and reinstall the blade. Replacing an affected part-numbered blade with a blade that has a S/N that is not subject to or has been excepted from the requirements of this AD, or that has an ‘‘R’’ code in the square block below the P/N field of the Data Plate, would be considered a terminating action for the requirements of this proposed AD. We estimate that this proposed AD would affect 156 helicopters of U.S. registry, and the proposed actions would require: PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 • Approximately 0.25 work hour for a pilot check, and 2 work hours for a maintenance inspection, at an average labor rate of $80 per work hour; • Approximately 6 work hours to remove and replace the blade; and • Parts, which would cost an estimated $13,410 per blade, assuming one blade per helicopter is replaced each year. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $3,090,360, assuming each helicopter would require 200 pilot checks and 12 maintenance inspections prior to replacing a blade on or before the compliance date for all affected helicopters. 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 a draft economic evaluation of the estimated costs to comply with this proposed AD. See the DMS to examine the draft economic evaluation. E:\FR\FM\28JYP1.SGM 28JYP1 Federal Register / Vol. 73, No. 145 / Monday, July 28, 2008 / Proposed Rules 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, 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: 43651 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by removing Amendment 39–13981 (70 FR 8021, February 17, 2005), and by adding a new airworthiness directive (AD), to read as follows: Bell Helicopter Textron Canada: Docket No. FAA–2008–0071; Directorate Identifier 2006–SW–27–AD. Supersedes AD 2005– 04–09, Amendment 39 13981, Docket No. FAA–2005–20107. Applicability: The following helicopter models, with a listed helicopter serial number (S/N) and a listed part-numbered tail rotor blade (blade) installed, that does not have an excepted S/N or code, certificated in any category. Helicopter model Helicopter S/N Blade part No. (P/N) 222 .................................................. 47006 through 47089 .................... 222B ................................................ 47131 through 47156 .................... 222U ................................................ 47501 through 47574 .................... 230 .................................................. 23001 through 23038 .................... 430 .................................................. 49001 through 49107 .................... 222–016–001–123, –123M, –127, –127M, –131, –135, –139M, –141M, except those P/Ns with S/Ns listed in Exceptions 1 and 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –127, –127M, –131, –135, –139M, –141M, except those P/Ns with S/Ns listed in Exceptions 1 and 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 2 or the ‘‘R’’ code described in Exception 3. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 2 or the ‘‘R’’ code described in Exception 3. yshivers on PROD1PC66 with PROPOSALS Exception 1: Blade, P/N 222–016– 001–135 or –141M, S/N A–1502, A– 1503, A–1504, A–1505, A–1507, A– 1508, A–1509, A–1510, A–1556, A– 1557, A–1558, A–1560, A–1561, A– 1574, A–1635, A–1636, A–1828, A– 1829, and S/Ns with a prefix of ‘‘A’’ and a number greater than 1829 have the intent of this proposal accomplished prior to delivery and no further action is required by this AD. Exception 2: Blade, P/N 222–016– 001–131 and –139M, S/N A–2049, A– 2055, A–2060, A–2070, A–2071, A– 2085, and S/Ns with a prefix of ‘‘A’’ and a number greater than 2085 have the VerDate Aug<31>2005 15:00 Jul 25, 2008 Jkt 214001 intent of this proposal accomplished prior to delivery and no further action is required by this AD. Exception 3: Blades identified with an ‘‘R’’ code in the square block below the P/N field of the Data Plate have already been modified and no further actions are required by this AD. Note 1: New blades, P/N 222–016–001–139 and –141, with no letter on the Data Plate after the P/N, are not subject to the requirements of this AD. Compliance: Required as indicated. To detect a crack in a blade, and to prevent loss of the blade and subsequent PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 loss of control of the helicopter, accomplish the following: (a) Within 3 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 3 hours TIS, clean and visually check both sides of each blade for a crack in the paint in the areas shown in Figure 1 of this AD. An owner/operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR sections 43.11 and 91.417(a)(2)(v). E:\FR\FM\28JYP1.SGM 28JYP1 Federal Register / Vol. 73, No. 145 / Monday, July 28, 2008 / Proposed Rules yshivers on PROD1PC66 with PROPOSALS Note 2: Bell Helicopter Textron Alert Service Bulletin (ASB) No. 222–04–100, Revision B, for Model 222 and 222B helicopters; ASB No. 222U–04–71, Revision B, for Model 222U helicopters; ASB No. 230– 04–31, Revision B, for Model 230 helicopters; and ASB No. 430–04–31, Revision C, for Model 430 helicopters, all dated March 31, 2008, pertain to the subject of this AD. (b) If the visual check required by paragraph (a) of this AD reveals a crack in the paint, before further flight, remove the blade and follow the requirements in paragraphs (c)(2) through (c)(3)(ii) of this AD. (c) Within the next 50 hours TIS, unless accomplished previously, and thereafter at intervals not to exceed 50 hours TIS, clean the blade by wiping down both surfaces of each blade in the inspection area depicted in Figure 1 of this AD using aliphatic naphtha (C–305) or detergent (C–318) or an equivalent. Using a 10X or higher power magnifying glass, visually inspect both sides of the blade in the areas depicted in Figure 1 of this AD. (1) If a crack is found, even if only in the paint, before further flight, remove the blade from the helicopter and proceed with the following: (2) Remove the paint on the blade down to the bare metal in the area of the suspected crack by using plastic media blasting (PMB) or a nylon web abrasive VerDate Aug<31>2005 15:00 Jul 25, 2008 Jkt 214001 pad. Abrade the blade surface in a spanwise direction only. Note 3: PMB may cause damage to helicopter parts if untrained personnel perform the paint removal. BHT–ALL–SPM, chapter 3, paragraph 3–24, pertains to the subject of this AD. (3) Using a 10X or higher power magnifying glass, inspect the blade for a crack. (i) If a crack is found, replace the blade with an airworthy blade before further flight. (ii) If no crack is found in the blade surface, refinish the blade by applying one coat of epoxy polyamide primer, MIL–P–23377 or MIL–P–85582, so that the primer overlaps the existing coats just beyond the abraded area. Let the area dry for 30 minutes to 1 hour. Then, apply one sealer coat of polyurethane, MILC85285 TYI CL2, color number 27925 (semi-gloss white), per Fed. Std. 595. Reinstall the blade. Note 4: BHT–ALL–SPM, chapter 4, pertains to painting the blade. (d) On or before 90 days after the effective date of this AD, replace any affected serial-numbered blade with an airworthy blade that has a S/N that is not subject to, or has been excepted from, the requirements of this AD. Installing an airworthy blade that is not subject to the requirements of this AD, PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 or has been excepted from the requirements of this AD, including those blades with an ‘‘R’’ code in the square block below the part number field of the Data Plate, constitute a terminating action for the requirements of this AD. (e) 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, Safety Management Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961, for information about previously approved alternative methods of compliance. Note 5: The subject of this AD is addressed in Transport Canada (Canada) AD CF–2004– 21R3, dated April 23, 2008. Issued in Fort Worth, Texas, on June 26, 2008. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–17261 Filed 7–25–08; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\28JYP1.SGM 28JYP1 EP28JY08.035</GPH> 43652

Agencies

[Federal Register Volume 73, Number 145 (Monday, July 28, 2008)]
[Proposed Rules]
[Pages 43648-43652]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17261]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0071; Directorate Identifier 2006-SW-27-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, 222U, 230, and 430 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes superseding an existing airworthiness 
directive (AD) for Bell Helicopter Textron Canada (BHTC) helicopters. 
That AD currently requires certain checks and inspections of the tail 
rotor blades. If a crack is found, the existing AD requires replacing 
the tail rotor blade (blade) with an airworthy blade before further 
flight. This action would require the same checks and inspections until 
they are required to be replaced and would remove certain serial 
numbered and specifically coded tail rotor blades from the 
applicability of the AD. This proposal is prompted by the approved 
rework of certain tail rotor blades and two newly redesigned tail rotor 
blades, which, if installed, constitutes terminating action for the 
inspection requirements. The actions specified by the proposed AD are 
intended to detect a crack in a blade, and to prevent loss of a blade 
and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before September 26, 2008.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     Federal eRulemaking Portal: Go to https://
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., 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

[[Page 43649]]

de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 
363-8023, fax (450) 433-0272.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at https://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy 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-2008-0071, 
Directorate Identifier 2006-SW-27-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://
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 the 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 19477-19478).

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Management 
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone 1-800-
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

    On February 10, 2005, we issued AD 2005-04-09, Amendment 39-13981 
(70 FR 8021, February 17, 2005), that superseded AD 2004-26-11, 
Amendment 39-13923 (70 FR 7, January 3, 2005), to require the 
following:
     Within 3 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 3 hours TIS, clean and visually check both 
sides of each blade for a crack in the area around the tail rotor 
feathering bearing. An owner/operator (pilot) may perform this check. 
Pilots may perform the checks required by paragraph (a) of this AD 
because they require no tools, can be done by observation, and can be 
done equally well by a pilot or a mechanic. However, the pilot must 
enter compliance with these requirements into the helicopter 
maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v).
     Within 50 hours TIS, and thereafter at intervals not to 
exceed 50 hours TIS, clean and inspect both sides of each blade for a 
crack using a 10X or higher magnifying glass.
     If a crack is found in the blade paint during a visual 
check or inspection, further inspect the blade as follows, before 
further flight:
     Remove the blade. Remove the paint to the bare metal in 
the area of the suspected crack by using plastic metal blasting (PMB) 
or a nylon web abrasive pad and abrading the blade surface in a span-
wise direction only. (The AD incorrectly used the word ``metal'' 
instead of ``media''.)
     Using a 10X or higher power magnifying glass, inspect the 
blade for a crack.
     If a crack is found, replace the blade with an airworthy 
blade before further flight.
     If no crack is found in the blade surface, refinish the 
blade by applying one coat of epoxy polyamide primer, MIL-P-23377 or 
MIL-P-85582, so that the primer overlaps the existing coats just beyond 
the abraded area. Let the area dry for 30 minutes to 1 hour. Then, 
apply one sealer coat of polyurethane, MILC85285 TYI CL2, color number 
27925 (semi-gloss white), per Fed. Std. 595, and reinstall the blade. 
That action was prompted by reports of cracked blades that were found 
during scheduled inspections. The requirements of that AD are intended 
to detect a crack in a blade, and to prevent loss of a blade and 
subsequent loss of control of the helicopter.
    AD 2005-04-09 required the same checks and inspections as AD 2004-
26-11, but also expands the applicability of AD 2004-26-11 to include 
two additional helicopter serial numbers.
    Since issuing AD 2005-04-09, BHTC has introduced a rework procedure 
for the affected tail rotor blades and two new part numbered tail rotor 
blades that eliminates the need for the recurring checks and 
inspections.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on the specified BHTC model 
helicopters. Transport Canada advises of the discovery of cracked 
blades during scheduled inspections on three occasions. Two cracks 
originated from the outboard feathering bearing bore underneath the 
flanged sleeves. The third crack started from the inboard feathering 
bearing bore. Investigation found that the cracks originated from 
either a machining burr or a corrosion site in the bearing bore 
underneath the flanged sleeves.
    BHTC has issued Alert Service Bulletin (ASB) No. 222-04-100, 
Revision B, for Model 222 and 222B helicopters; ASB No. 222U-04-71, 
Revision B, for Model 222U helicopters; ASB No. 230-04-31, Revision B, 
for Model 230 helicopters; and ASB No. 430-04-31, Revision C, for Model 
430 helicopters, all dated March 31, 2008. The ASBs specify a visual 
inspection of the blade root end around the feathering bearings for a 
crack, not later than at the next scheduled inspection, and thereafter 
at every 3 flight hours maximum. Further, they describe a visual 
inspection for a crack, to include removing the blade from the 
helicopter if a crack is found in the paint, within the next 50 flight 
hours, and thereafter at every 50 flight hours. In addition, the ASBs 
state that, on or before December 31, 2008, each blade should be 
reworked by Rotor Blades, Inc., or exchanged if the blade has less than 
4,000 hours TIS or if the blade has 4,000 or more hours TIS, the blade 
should continue to be repetitively inspected or a replacement blade 
should be ordered. Transport Canada classified these ASBs as mandatory 
and issued AD CF-2004-21R3, dated April 23, 2008, to ensure the 
continued airworthiness of these helicopters in Canada.
    This proposal differs from the ASB in that it would require, on or 
before 90 days after the effective date of the AD, replacing all 
affected tail rotor blades with airworthy tail rotor blades that are 
not subject to the proposed inspection requirements, without 
differentiating between blades based on hours TIS. Additionally, 
operators are not required to send their tail rotor blade to Rotor 
Blades, Inc. for rework.
    These helicopter models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada

[[Page 43650]]

has kept the FAA informed of the situation described above. The FAA has 
examined the findings of Transport Canada, reviewed all available 
information, and determined that AD action is necessary for products of 
these type designs that are certificated for operation in the United 
States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type designs. Therefore, the 
proposed AD would supersede AD 2005-04-09, and would apply as follows:

------------------------------------------------------------------------
                                Helicopter serial
       Helicopter model             No. (S/N)       Blade part No. (P/N)
------------------------------------------------------------------------
222...........................  47006 through      222-016-001-123, -
                                 47089.             123M, -127, -127M, -
                                                    131, -135, -139M, -
                                                    141M, except those P/
                                                    Ns with S/Ns listed
                                                    in Exceptions 1 and
                                                    2 or the ``R'' code
                                                    described in
                                                    Exception 3.
222B..........................  47131 through      222-016-001-123, -
                                 47156.             123M, -127, -127M, -
                                                    131, -135, -139M, -
                                                    141M, except those P/
                                                    Ns with S/Ns listed
                                                    in Exceptions 1 and
                                                    2 or the ``R'' code
                                                    described in
                                                    Exception 3.
222U..........................  47501 through      222-016-001-123, -
                                 47574.             123M, -131, -139M,
                                                    except those P/Ns
                                                    with a S/N listed in
                                                    Exception 2 or the
                                                    ``R'' code described
                                                    in Exception 3.
230...........................  23001 through      222-016-001-123, -
                                 23038.             123M, -131, -139M,
                                                    except those P/Ns
                                                    with a S/N listed in
                                                    Exception 2 or the
                                                    ``R'' code described
                                                    in Exception 3.
430...........................  49001 through      222-016-001-123, -
                                 49107.             123M, -131, -139M,
                                                    except those P/Ns
                                                    with a S/N listed in
                                                    Exception 2 or the
                                                    ``R'' code described
                                                    in Exception 3.
------------------------------------------------------------------------

    Exception 1: Blade, P/N 222-016-001-135 or -141M, S/N A-1502, A-
1503, A-1504, A-1505, A-1507, A-1508, A-1509, A-1510, A-1556, A-1557, 
A-1558, A-1560, A-1561, A-1574, A-1635, A-1636, A-1828, A-1829, and S/
Ns with a prefix of ``A'' and a number greater than 1829 have the 
intent of this proposal accomplished prior to delivery and no further 
action is required by this proposed AD.
    Exception 2: Blade, P/N 222-016-001-131 and -139M, S/N A-2049, A-
2055, A-2060, A-2070, A-2071, A-2085, and S/Ns with a prefix of ``A'' 
and a number greater than 2085 have the intent of this proposal 
accomplished prior to delivery and no further action is required by 
this proposed AD.
    Exception 3: Blades identified with an ``R'' code in the square 
block below the P/N field of the Data Plate have already been modified 
and no further actions are required by this proposed AD.

    Note 1: New blades, P/N 222-016-001-139 and -141, with no letter 
on the Data Plate after the P/N, are not subject to the requirements 
of this proposed AD.

    The proposed AD would require the following:
     Within 3 hours TIS, unless accomplished previously, and 
thereafter at intervals not to exceed 3 hours TIS, clean and visually 
check both sides of each blade for a crack in the area around the tail 
rotor feathering bearing. An owner/operator (pilot) holding at least a 
private pilot certificate may perform this check. Pilots may perform 
the checks required by paragraph (a) of this proposed AD because they 
require no tools, can be done by observation, and can be done equally 
well by a pilot or a mechanic. However, the pilot must enter compliance 
with these requirements into the helicopter maintenance records by 
following 14 CFR 43.11 and 91.417(a)(2)(v).
     Within 50 hours TIS, and thereafter at intervals not to 
exceed 50 hours TIS, clean and inspect both sides of each blade for a 
crack using a 10X or higher magnifying glass.
     If a crack is found in the blade paint during a visual 
check or inspection, further inspect the blade as follows, before 
further flight:
     Remove the blade. Remove the paint to the bare metal in 
the area of the suspected crack by using plastic media blasting (PMB) 
or a nylon web abrasive pad and abrading the blade surface in a span-
wise direction only.
     Using a 10X or higher power magnifying glass, inspect the 
blade for a crack.
     If a crack is found, replace the blade with an airworthy 
blade before further flight.
     If no crack is found in the blade surface, refinish the 
blade by applying one coat of epoxy polyamide primer, MIL-P-23377 or 
MIL-P-85582, so that the primer overlaps the existing coats just beyond 
the abraded area. Let the area dry for 30 minutes to 1 hour. Then, 
apply one sealer coat of polyurethane, MILC85285 TYI CL2, color number 
27925 (semi-gloss white), per Fed. Std. 595, and reinstall the blade.
    Replacing an affected part-numbered blade with a blade that has a 
S/N that is not subject to or has been excepted from the requirements 
of this AD, or that has an ``R'' code in the square block below the P/N 
field of the Data Plate, would be considered a terminating action for 
the requirements of this proposed AD.
    We estimate that this proposed AD would affect 156 helicopters of 
U.S. registry, and the proposed actions would require:
     Approximately 0.25 work hour for a pilot check, and 2 work 
hours for a maintenance inspection, at an average labor rate of $80 per 
work hour;
     Approximately 6 work hours to remove and replace the 
blade; and
     Parts, which would cost an estimated $13,410 per blade, 
assuming one blade per helicopter is replaced each year.
    Based on these figures, we estimate the total cost impact of the 
proposed AD on U.S. operators to be $3,090,360, assuming each 
helicopter would require 200 pilot checks and 12 maintenance 
inspections prior to replacing a blade on or before the compliance date 
for all affected helicopters.

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 a draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft economic 
evaluation.

[[Page 43651]]

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, 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 removing Amendment 39-13981 (70 FR 
8021, February 17, 2005), and by adding a new airworthiness directive 
(AD), to read as follows:

Bell Helicopter Textron Canada: Docket No. FAA-2008-0071; 
Directorate Identifier 2006-SW-27-AD. Supersedes AD 2005-04-09, 
Amendment 39 13981, Docket No. FAA-2005-20107.

    Applicability: The following helicopter models, with a listed 
helicopter serial number (S/N) and a listed part-numbered tail rotor 
blade (blade) installed, that does not have an excepted S/N or code, 
certificated in any category.

------------------------------------------------------------------------
       Helicopter model           Helicopter S/N    Blade part No. (P/N)
------------------------------------------------------------------------
222...........................  47006 through      222-016-001-123, -
                                 47089.             123M, -127, -127M, -
                                                    131, -135, -139M, -
                                                    141M, except those P/
                                                    Ns with S/Ns listed
                                                    in Exceptions 1 and
                                                    2 or the ``R'' code
                                                    described in
                                                    Exception 3.
222B..........................  47131 through      222-016-001-123, -
                                 47156.             123M, -127, -127M, -
                                                    131, -135, -139M, -
                                                    141M, except those P/
                                                    Ns with S/Ns listed
                                                    in Exceptions 1 and
                                                    2 or the ``R'' code
                                                    described in
                                                    Exception 3.
222U..........................  47501 through      222-016-001-123, -
                                 47574.             123M, -131, -139M,
                                                    except those P/Ns
                                                    with a S/N listed in
                                                    Exception 2 or the
                                                    ``R'' code described
                                                    in Exception 3.
230...........................  23001 through      222-016-001-123, -
                                 23038.             123M, -131, -139M,
                                                    except those P/Ns
                                                    with a S/N listed in
                                                    Exception 2 or the
                                                    ``R'' code described
                                                    in Exception 3.
430...........................  49001 through      222-016-001-123, -
                                 49107.             123M, -131, -139M,
                                                    except those P/Ns
                                                    with a S/N listed in
                                                    Exception 2 or the
                                                    ``R'' code described
                                                    in Exception 3.
------------------------------------------------------------------------

    Exception 1: Blade, P/N 222-016-001-135 or -141M, S/N A-1502, A-
1503, A-1504, A-1505, A-1507, A-1508, A-1509, A-1510, A-1556, A-1557, 
A-1558, A-1560, A-1561, A-1574, A-1635, A-1636, A-1828, A-1829, and S/
Ns with a prefix of ``A'' and a number greater than 1829 have the 
intent of this proposal accomplished prior to delivery and no further 
action is required by this AD.
    Exception 2: Blade, P/N 222-016-001-131 and -139M, S/N A-2049, A-
2055, A-2060, A-2070, A-2071, A-2085, and S/Ns with a prefix of ``A'' 
and a number greater than 2085 have the intent of this proposal 
accomplished prior to delivery and no further action is required by 
this AD.
    Exception 3: Blades identified with an ``R'' code in the square 
block below the P/N field of the Data Plate have already been modified 
and no further actions are required by this AD.

    Note 1: New blades, P/N 222-016-001-139 and -141, with no letter 
on the Data Plate after the P/N, are not subject to the requirements 
of this AD.

    Compliance: Required as indicated.
    To detect a crack in a blade, and to prevent loss of the blade and 
subsequent loss of control of the helicopter, accomplish the following:
    (a) Within 3 hours time-in-service (TIS), unless accomplished 
previously, and thereafter at intervals not to exceed 3 hours TIS, 
clean and visually check both sides of each blade for a crack in the 
paint in the areas shown in Figure 1 of this AD. An owner/operator 
(pilot), holding at least a private pilot certificate, may perform this 
visual check and must enter compliance with this paragraph into the 
helicopter maintenance records by following 14 CFR sections 43.11 and 
91.417(a)(2)(v).

[[Page 43652]]

[GRAPHIC] [TIFF OMITTED] TP28JY08.035


    Note 2: Bell Helicopter Textron Alert Service Bulletin (ASB) No. 
222-04-100, Revision B, for Model 222 and 222B helicopters; ASB No. 
222U-04-71, Revision B, for Model 222U helicopters; ASB No. 230-04-
31, Revision B, for Model 230 helicopters; and ASB No. 430-04-31, 
Revision C, for Model 430 helicopters, all dated March 31, 2008, 
pertain to the subject of this AD.

    (b) If the visual check required by paragraph (a) of this AD 
reveals a crack in the paint, before further flight, remove the blade 
and follow the requirements in paragraphs (c)(2) through (c)(3)(ii) of 
this AD.
    (c) Within the next 50 hours TIS, unless accomplished previously, 
and thereafter at intervals not to exceed 50 hours TIS, clean the blade 
by wiping down both surfaces of each blade in the inspection area 
depicted in Figure 1 of this AD using aliphatic naphtha (C-305) or 
detergent (C-318) or an equivalent. Using a 10X or higher power 
magnifying glass, visually inspect both sides of the blade in the areas 
depicted in Figure 1 of this AD.
    (1) If a crack is found, even if only in the paint, before further 
flight, remove the blade from the helicopter and proceed with the 
following:
    (2) Remove the paint on the blade down to the bare metal in the 
area of the suspected crack by using plastic media blasting (PMB) or a 
nylon web abrasive pad. Abrade the blade surface in a span-wise 
direction only.

    Note 3: PMB may cause damage to helicopter parts if untrained 
personnel perform the paint removal. BHT-ALL-SPM, chapter 3, 
paragraph 3-24, pertains to the subject of this AD.

    (3) Using a 10X or higher power magnifying glass, inspect the blade 
for a crack.
    (i) If a crack is found, replace the blade with an airworthy blade 
before further flight.
    (ii) If no crack is found in the blade surface, refinish the blade 
by applying one coat of epoxy polyamide primer, MIL-P-23377 or MIL-P-
85582, so that the primer overlaps the existing coats just beyond the 
abraded area. Let the area dry for 30 minutes to 1 hour. Then, apply 
one sealer coat of polyurethane, MILC85285 TYI CL2, color number 27925 
(semi-gloss white), per Fed. Std. 595. Reinstall the blade.

    Note 4: BHT-ALL-SPM, chapter 4, pertains to painting the blade.

    (d) On or before 90 days after the effective date of this AD, 
replace any affected serial-numbered blade with an airworthy blade that 
has a S/N that is not subject to, or has been excepted from, the 
requirements of this AD. Installing an airworthy blade that is not 
subject to the requirements of this AD, or has been excepted from the 
requirements of this AD, including those blades with an ``R'' code in 
the square block below the part number field of the Data Plate, 
constitute a terminating action for the requirements of this AD.
    (e) 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, Safety Management Group, FAA, ATTN: Sharon Miles, 
Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and 
Policy Group, Fort Worth, Texas 76193-0111, telephone (817) 222-5122, 
fax (817) 222-5961, for information about previously approved 
alternative methods of compliance.

    Note 5: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2004-21R3, dated April 23, 2008.


    Issued in Fort Worth, Texas, on June 26, 2008.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E8-17261 Filed 7-25-08; 8:45 am]
BILLING CODE 4910-13-P

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