Airworthiness Directives; Bell Helicopter Textron, Inc. (Bell) Model 204B, 205A, 205A-1, 205B, and 212 Helicopters, 67628-67631 [2011-28361]

Download as PDF 67628 Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Proposed Rules Issued in Renton, Washington, on October 21, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–28368 Filed 11–1–11; 8:45 a.m.] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1188; Directorate Identifier 2008–SW–46–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron, Inc. (Bell) Model 204B, 205A, 205A–1, 205B, and 212 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This document proposes superseding four existing airworthiness directives (ADs) for the specified Bell model helicopters. Two of the existing ADs require an initial and repetitive inspection of certain part-numbered main rotor yokes installed on Bell Model 204B, 205A–1, and 212 helicopters. Two other existing ADs also establish a retirement life of 3,600 hours time-in-service (TIS) for certain partnumbered main rotor yokes installed on the Bell Model 204, 205 series, and 212 series helicopters. Those ADs were prompted by reports of cracks in the main rotor yoke (yoke). This action would retain the requirements of the existing ADs and would apply these inspections and retirement lives to additional part-numbered yokes. This action would also increase the inspection frequency for certain yokes installed on a Bell Model 205B or 212 helicopter and would require replacing any unairworthy yoke. This proposal is prompted by the need to expand the applicability to include yokes produced under a Parts Manufacturing Approval (PMA) whose design approval was based on identicality with the affected Bell yoke parts and a recent discovery of a cracked yoke. The actions specified by the proposed AD are intended to prevent cracking of a yoke, failure of the yoke, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before January 3, 2012. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:10 Nov 01, 2011 Jkt 226001 • 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, Inc., P.O. Box 482, Fort Worth, TX 76101, telephone (817) 280–3391, fax (817) 280–6466, or at https://www.bellcustomer.com/files/. FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76137, 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–2011–1188, Directorate Identifier 2008–SW–46–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 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 DOTs complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information on the PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 internet at https://www.regulations.gov or 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 On September 13, 1979, we issued AD 79–20–05, Docket No. 79–ASW–25, Amendment 39–3572 (44 FR 55556, September 27, 1979) for Bell Model 204B, 205A–1, and 212 helicopters. That AD requires an initial and repetitive inspection at 2,400-hour intervals and corrosion protection and sealing of the yoke, P/N 204–011–102, of the main rotor hub assembly (hub), P/N 204–012–101. We issued Amendment 39–3626, November 21, 1979 (44 FR 70123, December 6, 1979) and Amendment 39–3662 January 3, 1980 (45 FR 6922, January 31, 1980) to AD 79–20–05. The amendments to the AD deleted references to the radius in the bottom of the pillow block bushing holes because the cracks did not initiate there. The cracks originated in the side of the hole near the top or through the center section of the yoke adjacent to the data plate. On August 26, 1981, we issued AD 81–19–01, Amendment 39–4207, Docket 81–ASW–38 (46 FR 45595, September 14, 1981) for Bell Model 212 series helicopters. We also issued AD 81–19– 02, Amendment 39–4208, Docket 81– ASW–40 (46 FR 45595, September 14, 1981) for Bell Model 204 and 205 series helicopters. These ADs established a retirement life of 3,600 hours TIS for certain yokes installed on these model helicopters. These yokes previously did not have a retirement life. AD 81–19–01 also reduced the yoke retirement life below 3,600 hours TIS for those yokes installed on Model 212 helicopters used in external load operations involving more than four lifts per hour by requiring the operators to log additional hours for these type operations against the retirement life of the yoke. These ADs were prompted by three field reports of cracked yokes. These ADs were intended to establish retirement lives to prevent yoke failure and subsequent loss of control of the helicopter. On March 4, 1993, we issued AD 93– 05–01, Amendment 39–8507, Docket No. 92–ASW–13 (58 FR 13700, March 15, 1993), for the Bell Model 212 helicopters to require repetitive inspections of yoke, P/N 204–011–102 E:\FR\FM\02NOP1.SGM 02NOP1 mstockstill on DSK4VPTVN1PROD with PROPOSALS Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Proposed Rules (all dash numbers). That action was prompted by 12 reports of cracking at the pillow block holes on yokes installed on Model 212 helicopters. That AD was intended to detect corrosion pitting and a crack in the pillow block bolt bushing holes of the yoke and to prevent failure of the main rotor system and subsequent loss of control of the helicopter. After issuing ADs 79–20–05, 81–19– 01, and 81–19–02, Bell has introduced a replacement stainless steel yoke, P/N 212–011–102. Bell issued Alert Service Bulletins (ASBs) Nos. 204–92–36, 205– 92–51, and 212–92–80, all dated October 23, 1992. The ASBs specify replacing the yoke, P/N 204–011–102 (all dash numbers), by December 31, 1993. These ASBs also specify replacing the yoke with yoke, P/N 212–011–102– 105 or –109, depending on the helicopter configuration. The replacement stainless steel yokes have improved design characteristics addressing the corrosion problems and are not subject to any heavy lift cycle counting required for previous yokes installed on the Model 205B and 212 helicopters. The FAA also issued PMAs to Air Services International (ASI) for yokes, P/N ASI–4011–102, and to Arizona Aeroparts International (AAI) for yokes, P/N AAI–4011–102, both based on identicality with the Bell-manufactured yoke, P/N 204–011–102. The yokes manufactured under the PMAs are eligible for installation on Bell Model 204B, 205A, 205A–1, and 212 helicopters. Transport Canada recently contacted the FAA about a PMA yoke, P/N AAI– 4011–102–125, manufactured by AAI. A Canadian operator reported this part was no longer supported by the PMAmanufacturer. The Canadian operator was trying to determine if the inspections in the existing ADs applicable to the Bell yoke, P/N 204– 011–102, needed to be performed on the PMA-manufactured yokes as well. Both of these PMA companies have gone out of business. There is no longer an FAAapproved PMA holder for these PMA yokes. This results in no continued operational safety oversight of the PMA parts by the manufacturer that produced the parts that were sold to operators. Because the PMA yokes are identical to the Bell parts, these yokes are susceptible to the same cracking conditions found in the same Bell partnumbered yokes. This AD action proposes to give operators credit for the accumulated operating time on yokes, P/N 204–011– 102 (all dash numbers), previously determined and recorded by following VerDate Mar<15>2010 17:10 Nov 01, 2011 Jkt 226001 ADs 81–19–01 or 81–19–02; or the applicable Bell Model 204B, 205A–1, 205B, or 212 maintenance manuals, which results in equal or higher accumulated factored hours TIS. However, these values must be included for previously accumulated service time in the calculations of the accumulated total factored hours TIS. Any additional factored hours TIS would be determined for each yoke using the hours TIS factors in the proposed AD. This proposal is prompted by the need to expand the applicability to include yokes produced under a PMA whose design approval was based on identicality with the affected Bell yoke parts and also a recent discovery of a cracked yoke on a Bell Model 212 helicopter. The previously described unsafe condition is likely to exist or develop on other helicopters of these same type designs. We estimate 25 to 30 of the yokes manufactured under a PMA may still be installed on helicopters operating in the U.S. Therefore, the proposed AD would supersede the previously issued ADs and would require: • For helicopters with yoke, P/N AAI–4011–102 (all dash numbers) and ASI–4011–102 (all dash numbers), installed, within 100 hours TIS, unless accomplished previously, creating a component history card or equivalent record for each yoke; determining the model for each helicopter on which the yoke has been installed from the time the yoke had zero hours TIS; calculating the factored hours TIS for each type of operation and rate of external load lifts and takeoffs for each hour TIS accumulated on each yoke; and recording the accumulated total factored hours TIS on the component history card or equivalent record for each yoke. Continuing to factor the hours TIS for each yoke and recording the additional factored hours TIS on the component history card or equivalent record. Tracking these factored hours TIS is only for the purpose of establishing a retirement life and not to be counted against the hours TIS used to track inspection intervals. • For helicopters with yoke, P/N 204– 011–102 (all dash numbers), installed, before further flight, unless accomplished previously: Æ Calculating the total factored hours TIS on the yoke for hours TIS accumulated before the effective date of this AD using the same requirements as ADs 81–19–01 and 81–19–02, which establishes the starting point for the new factoring of hours TIS contained in this AD. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 67629 Æ Calculating and recording the factored hours TIS on the yoke for hours TIS accumulated after the effective date of this AD using the same requirements as used for calculating the total factored hours TIS in this AD for yokes, P/N AAI–4011–102 (all dash numbers) and ASI–4011–102 (all dash numbers). • Revising the Airworthiness Limitations section of the applicable maintenance manuals or the Instructions for Continued Airworthiness (ICAs) by establishing or continuing a retirement life of 3,600 Total Factored Hours TIS for each yoke. • Recording a life limit of 3,600 Total Factored Hours TIS for each yoke on the component history card or equivalent record. • Within 100 hours TIS or 600 hours TIS since the last magnetic particle inspection (MPI) of the yoke, whichever occurs later, and thereafter at intervals not to exceed 600 hours TIS, for any yoke installed on any Model 205B or 212 helicopter: Æ Removing the yoke from the hub. Using a 5-power or higher magnifying glass, visually inspecting each pillow block bushing hole, spindle radius, and center section web for any corrosion or mechanical damage. Æ Performing an MPI of each yoke for a crack. • Within 100 hours TIS or 2,400 hours TIS since the last MPI of the yoke, whichever occurs later, and thereafter at intervals not to exceed 2,400 hours TIS, for any yoke installed on any Model 204B, 205A, or 205A–1 helicopter: Æ Removing the yoke from the hub. Using a 5-power or higher magnifying glass, visually inspect each pillow block bushing hole, spindle radius, and center section web for any corrosion or mechanical damage. Æ Performing an MPI of each yoke for a crack. • Before further flight, replacing each yoke with an airworthy yoke if: Æ The yoke has 3,600 or more Total Factored Hours TIS; Æ The Total Factored Hours TIS for the yoke is unknown and cannot be determined; Æ The yoke has any corrosion or mechanical damage that exceeds any of the maximum repair damage limits; or Æ The yoke has a crack. We estimate that this proposed AD would affect about 15 helicopters of U.S. registry and would take about: • 3 work hours to review the helicopter records and determine the total factored hours TIS (the cost of tracking the total factored flight hours will be negligible), • 35 work hours to remove the yoke from the helicopter and do a visual inspection and MPI, and E:\FR\FM\02NOP1.SGM 02NOP1 67630 Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Proposed Rules • 32 work hours to replace a yoke, at an average labor rate of $85 per work hour per helicopter. • Required parts would cost about $40,157 per helicopter. Based on these figures, we estimate the total cost of the proposed AD on U.S. operators to be $48,450, assuming 15 helicopters have a yoke installed requiring a review of the helicopter records and to determine the hours TIS with one visual inspection and MPI, and no yoke needs to be replaced. If we assume all the yokes in the fleet are replaced, the total cost would be about $643,155. 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 AD docket to examine the draft economic evaluation. 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. § 39.13 [Amended] 2. Section 39.13 is amended by removing Amendments 39–8507 (58 FR 13700, March 15, 1993); 39–4208 (46 FR 45595, September 14, 1981); 39–4207 (46 FR 45595, September 14, 1981); 39– 3662 (45 FR 6922, January 31, 1980); 39–3626 (44 FR 70123, December 6, 1979); and 39–3572 (44 FR 55556, September 27, 1979); and by adding a new airworthiness directive (AD) to read as follows: Bell Helicopter Textron, Inc (Bell): Docket No. FAA–2011–1188; Directorate Identifier 2008–SW–46–AD. Supersedes AD 93–05–01, Amendment 39–8507, Docket No. 92–ASW–13; AD 81–19–02, Amendment 39–4208, Docket No. 81– ASW–40; AD 81–19–01, Amendment 394207, Docket No. 81–ASW–38; and AD 79–20–05, Amendments 39–3662, 39– 3626, and 39–3572, Docket No. 79– ASW–25. Applicability: Model 204B, 205A, 205A–1, 205B, and 212 helicopters, with a main rotor yoke (yoke), part number (P/N) AAI–4011– 102 (all dash numbers), ASI–4011–102 (all dash numbers), or 204–011–102 (all dash numbers), installed, certificated in any category. Compliance: Required as indicated. To prevent cracking of a yoke, failure of a yoke, and subsequent loss of control of the helicopter, do the following: (a) For helicopters with yoke, P/N AAI– 4011–102 (all dash numbers) and ASI–4011– 102 (all dash numbers), installed, within 100 hours time-in-service (TIS), unless accomplished previously: (1) Create a component history card or equivalent record for each yoke. (2) Determine the model for each helicopter on which the yoke has been installed from the time the yoke had zero hours TIS. (3) In accordance with the rate per hour categories shown in Table 1 of this AD, categorize the accumulated ‘‘Unfactored Hours TIS’’ on each yoke by determining the types of operation AND the rate per hour of external load lifts and takeoffs for each hour TIS accumulated on each yoke. One external load lift occurs each time the helicopter picks up an external load and drops it off. For determining the proper rate per hour category for external load operations, any external load lift in which the helicopter achieves a vertical altitude difference of greater than 200 feet indicated altitude between the pickup and drop-off point counts as two external load lifts. TABLE 1—FACTORED HOURS TIS FOR A YOKE Factored hours TIS on yoke (unfactored hours TIS × hours TIS factor) mstockstill on DSK4VPTVN1PROD with PROPOSALS Helicopter model Types of operation Rate per hour of external load lifts and takeoffs Yokes installed on any Model 204B, 205A, or 205A–1 helicopter. Yokes installed on any Model 205B or 212 helicopter. All Operations ............ All .............................. 120 1 120 External Load Operations 1. 1 to 5 ......................... 105 1 105 5.1 to 8 ...................... 8.1 to 12 .................... 12.1 to 18 .................. 18.1 to 32 .................. 32.1 to 48 .................. 48.1 or above ............ Unknown ................... .................... .................... .................... 170 .................... .................... 50 1.5 2 3 5 7 9 7 .............................. .............................. .............................. 850 .............................. .............................. 350 VerDate Mar<15>2010 17:10 Nov 01, 2011 Jkt 226001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Unfactored hours TIS E:\FR\FM\02NOP1.SGM Hours TIS factor 02NOP1 Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Proposed Rules 67631 TABLE 1—FACTORED HOURS TIS FOR A YOKE—Continued Factored hours TIS on yoke (unfactored hours TIS × hours TIS factor) Unfactored hours TIS Internal Load Operations. Helicopter model Rate per hour of external load lifts and takeoffs All Takeoffs ............... 2,025 1 2,025 .................................... .................................... .................... .................... 3,450 Types of operation Total Factored Hours TIS on Yoke (Summation of the Factored Hours TIS). Hours TIS factor 1 For the purposes of this AD, an external load operation occurs each time a helicopter picks up an external load and drops it off. Any external load lift in which the helicopter achieves a vertical altitude difference of greater than 200 feet indicated attitude between the pick-up and drop-off point counts as two external load lifts in determining the proper rate per hour category. mstockstill on DSK4VPTVN1PROD with PROPOSALS Note 1: The number of unfactored hours TIS and factored hours TIS contained in Table 1 of this AD are examples and presented for illustration purposes only. (4) By reference to Table 1 of this AD, enter the ‘‘Unfactored Hours TIS’’ for each category as determined by paragraph (a)(3) of this AD. Calculate the ‘‘Factored Hours TIS’’ by multiplying the ‘‘Unfactored Hours TIS’’ by the ‘‘Hours TIS Factor.’’ Determine the accumulated ‘‘Total Factored Hours TIS’’ on each yoke by adding the factored hours TIS for each type of operation and helicopter model. Tracking the Total Factored Hours TIS is only for establishing a retirement life and not for tracking inspection intervals. (5) Record the accumulated Total Factored Hours TIS on the component history card or equivalent record for each yoke. (6) Continue to factor the hours TIS for each yoke by following paragraph (a)(2) through (a)(4) of this AD, and record the additional factored hours TIS on the component history card or equivalent record. (b) For helicopters with yoke, P/N 204– 011–102 (all dash numbers), installed, before further flight, unless accomplished previously: (1) For hours TIS accumulated before the effective date of this AD, calculate and record the Total Factored Hours TIS as follows: (i) For the Model 212 helicopters, 1 hour TIS in which passenger or internal cargo was carried equals 1 factored hour TIS; 1 hour TIS where more than 4 external load lifts occurred equals 5 factored hours TIS. (ii) For the Model 204 and 205 series helicopters, 1 hour TIS equals 1 factored hour TIS. Note 2: Paragraph (b)(1) gives credit to the operators for compliance with ADs 81–19–01 and 81–19–02 in establishing the starting point for the new factoring of hours TIS contained in this AD. Note 3: The accumulated Total Factored Hours TIS for yoke, P/N 204–011–102 (all dash numbers), calculated in accordance with the applicable Bell Model 204B, 205A– 1, 205B, or 212 maintenance manuals, which results in an equal or higher accumulated Total Factored Hours TIS is an acceptable alternative to meeting the factoring requirements of AD 81–19–01 (contained in Bell ASB 212–81–23, dated June 22, 1981, for the Model 212 helicopters) and AD 81–19– 02 (contained in Bell ASBs 204–81–11 and VerDate Mar<15>2010 17:10 Nov 01, 2011 Jkt 226001 205–81–16, both dated June 22, 1981, for the Model 204 and 205 series helicopters). (2) For hours TIS accumulated after the effective date of this AD, calculate and record the factored hours TIS on the yoke in accordance with the requirements of paragraphs (a)(1) thorough (a)(6) of this AD. (c) Revise the Airworthiness Limitations section of the applicable maintenance manuals or the Instructions for Continued Airworthiness (ICAs) by establishing a new retirement life of 3,600 Total Factored Hours TIS for each yoke, P/N AAI–4011–102 (all dash numbers), ASI–4011–102 (all dash numbers), or 204–011–102 (all dash numbers), by making pen and ink changes or inserting a copy of this AD into the Airworthiness Limitations section of the maintenance manual or ICAs. (d) Unless accomplished previously, record a life limit of 3,600 Total Factored Hours TIS for each yoke, P/N AAI–4011–102 (all dash numbers), ASI–4011–102 (all dash numbers), or 204–011–102 (all dash numbers), on the component history card or equivalent record. (e) Within 100 hours TIS or 600 hours TIS since the last magnetic particle inspection (MPI) of the yoke, whichever occurs later, and thereafter at intervals not to exceed 600 hours TIS, for any yoke installed on any Model 205B or 212 helicopter: (1) Remove the yoke from the main rotor hub assembly (hub). Using a 5-power or higher magnifying glass, visually inspect each pillow block bushing hole, spindle radius, and center section web for any corrosion or mechanical damage. (2) Perform an MPI of each yoke for a crack. Note 4: MPI procedures are contained in Bell Standard Practices Manual BHT–ALL– SPM. (f) Within 100 hours TIS or 2,400 hours TIS since the last MPI of the yoke, whichever occurs later, and thereafter at intervals not to exceed 2,400 hours TIS, for any yoke installed on any Model 204B, 205A, or 205A– 1 helicopter: (1) Remove the yoke from the hub. Using a 5-power or higher magnifying glass, visually inspect each pillow block bushing hole, spindle radius, and center section web for any corrosion or mechanical damage. (2) Perform an MPI of each yoke for a crack. (g) Before further flight, replace each yoke with an airworthy yoke if: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 (1) The yoke has 3,600 or more Total Factored Hours TIS; or (2) The Total Factored Hours TIS for the yoke is unknown and cannot be determined; or (3) The yoke has any corrosion or mechanical damage that exceeds any of the maximum repair damage limits; or Note 5: The applicable Bell Component and Repair Overhaul Manual contains the maximum repair damage limitations. (4) The yoke has a crack. (h) 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, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222– 5170, fax (817) 222–5783, for information about previously approved alternative methods of compliance. (i) Special flight permits may only be issued under 14 CFR 21.197 and 21.199 for the purpose of operating the helicopter to a location where the MPI requirements of paragraphs (e) or (f) of this AD can be performed. (j) The Joint Aircraft System Component (JASC) Code is 6220: Main Rotor Head Issued in Fort Worth, Texas, on October 21, 2011. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–28361 Filed 11–1–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1212; Directorate Identifier 2011–CE–034–AD] RIN 2120–AA64 Airworthiness Directives; Cirrus Design Corporation Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\02NOP1.SGM 02NOP1

Agencies

[Federal Register Volume 76, Number 212 (Wednesday, November 2, 2011)]
[Proposed Rules]
[Pages 67628-67631]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-28361]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1188; Directorate Identifier 2008-SW-46-AD]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron, Inc. (Bell)
Model 204B, 205A, 205A-1, 205B, and 212 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes superseding four existing airworthiness
directives (ADs) for the specified Bell model helicopters. Two of the
existing ADs require an initial and repetitive inspection of certain
part-numbered main rotor yokes installed on Bell Model 204B, 205A-1,
and 212 helicopters. Two other existing ADs also establish a retirement
life of 3,600 hours time-in-service (TIS) for certain part-numbered
main rotor yokes installed on the Bell Model 204, 205 series, and 212
series helicopters. Those ADs were prompted by reports of cracks in the
main rotor yoke (yoke). This action would retain the requirements of
the existing ADs and would apply these inspections and retirement lives
to additional part-numbered yokes. This action would also increase the
inspection frequency for certain yokes installed on a Bell Model 205B
or 212 helicopter and would require replacing any unairworthy yoke.
This proposal is prompted by the need to expand the applicability to
include yokes produced under a Parts Manufacturing Approval (PMA) whose
design approval was based on identicality with the affected Bell yoke
parts and a recent discovery of a cracked yoke. The actions specified
by the proposed AD are intended to prevent cracking of a yoke, failure
of the yoke, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before January 3, 2012.

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, Inc., P.O. Box 482, Fort Worth, TX 76101,
telephone (817) 280-3391, fax (817) 280-6466, or at https://www.bellcustomer.com/files/.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
2601 Meacham Blvd., Fort Worth, Texas 76137, 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-2011-1188,
Directorate Identifier 2008-SW-46-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 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 DOTs complete
Privacy Act Statement in the Federal Register published on April 11,
2000 (65 FR 19477-78).

Examining the Docket

You may examine the docket that contains the proposed AD, any
comments, and other information on the internet at https://www.regulations.gov or 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

On September 13, 1979, we issued AD 79-20-05, Docket No. 79-ASW-25,
Amendment 39-3572 (44 FR 55556, September 27, 1979) for Bell Model
204B, 205A-1, and 212 helicopters. That AD requires an initial and
repetitive inspection at 2,400-hour intervals and corrosion protection
and sealing of the yoke, P/N 204-011-102, of the main rotor hub
assembly (hub), P/N 204-012-101. We issued Amendment 39-3626, November
21, 1979 (44 FR 70123, December 6, 1979) and Amendment 39-3662 January
3, 1980 (45 FR 6922, January 31, 1980) to AD 79-20-05. The amendments
to the AD deleted references to the radius in the bottom of the pillow
block bushing holes because the cracks did not initiate there. The
cracks originated in the side of the hole near the top or through the
center section of the yoke adjacent to the data plate.
On August 26, 1981, we issued AD 81-19-01, Amendment 39-4207,
Docket 81-ASW-38 (46 FR 45595, September 14, 1981) for Bell Model 212
series helicopters. We also issued AD 81-19-02, Amendment 39-4208,
Docket 81-ASW-40 (46 FR 45595, September 14, 1981) for Bell Model 204
and 205 series helicopters. These ADs established a retirement life of
3,600 hours TIS for certain yokes installed on these model helicopters.
These yokes previously did not have a retirement life. AD 81-19-01 also
reduced the yoke retirement life below 3,600 hours TIS for those yokes
installed on Model 212 helicopters used in external load operations
involving more than four lifts per hour by requiring the operators to
log additional hours for these type operations against the retirement
life of the yoke. These ADs were prompted by three field reports of
cracked yokes. These ADs were intended to establish retirement lives to
prevent yoke failure and subsequent loss of control of the helicopter.
On March 4, 1993, we issued AD 93-05-01, Amendment 39-8507, Docket
No. 92-ASW-13 (58 FR 13700, March 15, 1993), for the Bell Model 212
helicopters to require repetitive inspections of yoke, P/N 204-011-102

[[Page 67629]]

(all dash numbers). That action was prompted by 12 reports of cracking
at the pillow block holes on yokes installed on Model 212 helicopters.
That AD was intended to detect corrosion pitting and a crack in the
pillow block bolt bushing holes of the yoke and to prevent failure of
the main rotor system and subsequent loss of control of the helicopter.
After issuing ADs 79-20-05, 81-19-01, and 81-19-02, Bell has
introduced a replacement stainless steel yoke, P/N 212-011-102. Bell
issued Alert Service Bulletins (ASBs) Nos. 204-92-36, 205-92-51, and
212-92-80, all dated October 23, 1992. The ASBs specify replacing the
yoke, P/N 204-011-102 (all dash numbers), by December 31, 1993. These
ASBs also specify replacing the yoke with yoke, P/N 212-011-102-105 or
-109, depending on the helicopter configuration. The replacement
stainless steel yokes have improved design characteristics addressing
the corrosion problems and are not subject to any heavy lift cycle
counting required for previous yokes installed on the Model 205B and
212 helicopters.
The FAA also issued PMAs to Air Services International (ASI) for
yokes, P/N ASI-4011-102, and to Arizona Aeroparts International (AAI)
for yokes, P/N AAI-4011-102, both based on identicality with the Bell-
manufactured yoke, P/N 204-011-102. The yokes manufactured under the
PMAs are eligible for installation on Bell Model 204B, 205A, 205A-1,
and 212 helicopters.
Transport Canada recently contacted the FAA about a PMA yoke, P/N
AAI-4011-102-125, manufactured by AAI. A Canadian operator reported
this part was no longer supported by the PMA-manufacturer. The Canadian
operator was trying to determine if the inspections in the existing ADs
applicable to the Bell yoke, P/N 204-011-102, needed to be performed on
the PMA-manufactured yokes as well. Both of these PMA companies have
gone out of business. There is no longer an FAA-approved PMA holder for
these PMA yokes. This results in no continued operational safety
oversight of the PMA parts by the manufacturer that produced the parts
that were sold to operators. Because the PMA yokes are identical to the
Bell parts, these yokes are susceptible to the same cracking conditions
found in the same Bell part-numbered yokes.
This AD action proposes to give operators credit for the
accumulated operating time on yokes, P/N 204-011-102 (all dash
numbers), previously determined and recorded by following ADs 81-19-01
or 81-19-02; or the applicable Bell Model 204B, 205A-1, 205B, or 212
maintenance manuals, which results in equal or higher accumulated
factored hours TIS. However, these values must be included for
previously accumulated service time in the calculations of the
accumulated total factored hours TIS. Any additional factored hours TIS
would be determined for each yoke using the hours TIS factors in the
proposed AD.
This proposal is prompted by the need to expand the applicability
to include yokes produced under a PMA whose design approval was based
on identicality with the affected Bell yoke parts and also a recent
discovery of a cracked yoke on a Bell Model 212 helicopter.
The previously described unsafe condition is likely to exist or
develop on other helicopters of these same type designs. We estimate 25
to 30 of the yokes manufactured under a PMA may still be installed on
helicopters operating in the U.S. Therefore, the proposed AD would
supersede the previously issued ADs and would require:
For helicopters with yoke, P/N AAI-4011-102 (all dash
numbers) and ASI-4011-102 (all dash numbers), installed, within 100
hours TIS, unless accomplished previously, creating a component history
card or equivalent record for each yoke; determining the model for each
helicopter on which the yoke has been installed from the time the yoke
had zero hours TIS; calculating the factored hours TIS for each type of
operation and rate of external load lifts and takeoffs for each hour
TIS accumulated on each yoke; and recording the accumulated total
factored hours TIS on the component history card or equivalent record
for each yoke. Continuing to factor the hours TIS for each yoke and
recording the additional factored hours TIS on the component history
card or equivalent record. Tracking these factored hours TIS is only
for the purpose of establishing a retirement life and not to be counted
against the hours TIS used to track inspection intervals.
For helicopters with yoke, P/N 204-011-102 (all dash
numbers), installed, before further flight, unless accomplished
previously:
[cir] Calculating the total factored hours TIS on the yoke for
hours TIS accumulated before the effective date of this AD using the
same requirements as ADs 81-19-01 and 81-19-02, which establishes the
starting point for the new factoring of hours TIS contained in this AD.
[cir] Calculating and recording the factored hours TIS on the yoke
for hours TIS accumulated after the effective date of this AD using the
same requirements as used for calculating the total factored hours TIS
in this AD for yokes, P/N AAI-4011-102 (all dash numbers) and ASI-4011-
102 (all dash numbers).
Revising the Airworthiness Limitations section of the
applicable maintenance manuals or the Instructions for Continued
Airworthiness (ICAs) by establishing or continuing a retirement life of
3,600 Total Factored Hours TIS for each yoke.
Recording a life limit of 3,600 Total Factored Hours TIS
for each yoke on the component history card or equivalent record.
Within 100 hours TIS or 600 hours TIS since the last
magnetic particle inspection (MPI) of the yoke, whichever occurs later,
and thereafter at intervals not to exceed 600 hours TIS, for any yoke
installed on any Model 205B or 212 helicopter:
[cir] Removing the yoke from the hub. Using a 5-power or higher
magnifying glass, visually inspecting each pillow block bushing hole,
spindle radius, and center section web for any corrosion or mechanical
damage.
[cir] Performing an MPI of each yoke for a crack.
Within 100 hours TIS or 2,400 hours TIS since the last MPI
of the yoke, whichever occurs later, and thereafter at intervals not to
exceed 2,400 hours TIS, for any yoke installed on any Model 204B, 205A,
or 205A-1 helicopter:
[cir] Removing the yoke from the hub. Using a 5-power or higher
magnifying glass, visually inspect each pillow block bushing hole,
spindle radius, and center section web for any corrosion or mechanical
damage.
[cir] Performing an MPI of each yoke for a crack.
Before further flight, replacing each yoke with an
airworthy yoke if:
[cir] The yoke has 3,600 or more Total Factored Hours TIS;
[cir] The Total Factored Hours TIS for the yoke is unknown and
cannot be determined;
[cir] The yoke has any corrosion or mechanical damage that exceeds
any of the maximum repair damage limits; or
[cir] The yoke has a crack.
We estimate that this proposed AD would affect about 15 helicopters
of U.S. registry and would take about:
3 work hours to review the helicopter records and
determine the total factored hours TIS (the cost of tracking the total
factored flight hours will be negligible),
35 work hours to remove the yoke from the helicopter and
do a visual inspection and MPI, and

[[Page 67630]]

32 work hours to replace a yoke, at an average labor rate
of $85 per work hour per helicopter.
Required parts would cost about $40,157 per helicopter.

Based on these figures, we estimate the total cost of the proposed AD
on U.S. operators to be $48,450, assuming 15 helicopters have a yoke
installed requiring a review of the helicopter records and to determine
the hours TIS with one visual inspection and MPI, and no yoke needs to
be replaced. If we assume all the yokes in the fleet are replaced, the
total cost would be about $643,155.

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 AD docket to examine the draft
economic evaluation.

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 Amendments 39-8507 (58 FR
13700, March 15, 1993); 39-4208 (46 FR 45595, September 14, 1981); 39-
4207 (46 FR 45595, September 14, 1981); 39-3662 (45 FR 6922, January
31, 1980); 39-3626 (44 FR 70123, December 6, 1979); and 39-3572 (44 FR
55556, September 27, 1979); and by adding a new airworthiness directive
(AD) to read as follows:

Bell Helicopter Textron, Inc (Bell): Docket No. FAA-2011-1188;
Directorate Identifier 2008-SW-46-AD. Supersedes AD 93-05-01,
Amendment 39-8507, Docket No. 92-ASW-13; AD 81-19-02, Amendment 39-
4208, Docket No. 81-ASW-40; AD 81-19-01, Amendment 39- 4207, Docket
No. 81-ASW-38; and AD 79-20-05, Amendments 39-3662, 39-3626, and 39-
3572, Docket No. 79-ASW-25.

Applicability: Model 204B, 205A, 205A-1, 205B, and 212
helicopters, with a main rotor yoke (yoke), part number (P/N) AAI-
4011-102 (all dash numbers), ASI-4011-102 (all dash numbers), or
204-011-102 (all dash numbers), installed, certificated in any
category.
Compliance: Required as indicated.
To prevent cracking of a yoke, failure of a yoke, and subsequent
loss of control of the helicopter, do the following:
(a) For helicopters with yoke, P/N AAI-4011-102 (all dash
numbers) and ASI-4011-102 (all dash numbers), installed, within 100
hours time-in-service (TIS), unless accomplished previously:
(1) Create a component history card or equivalent record for
each yoke.
(2) Determine the model for each helicopter on which the yoke
has been installed from the time the yoke had zero hours TIS.
(3) In accordance with the rate per hour categories shown in
Table 1 of this AD, categorize the accumulated ``Unfactored Hours
TIS'' on each yoke by determining the types of operation AND the
rate per hour of external load lifts and takeoffs for each hour TIS
accumulated on each yoke. One external load lift occurs each time
the helicopter picks up an external load and drops it off. For
determining the proper rate per hour category for external load
operations, any external load lift in which the helicopter achieves
a vertical altitude difference of greater than 200 feet indicated
altitude between the pickup and drop-off point counts as two
external load lifts.

Table 1--Factored Hours TIS for a Yoke
----------------------------------------------------------------------------------------------------------------
Factored hours
Rate per hour of TIS on yoke
Helicopter model Types of external load Unfactored Hours TIS (unfactored hours
operation lifts and hours TIS factor TIS x hours TIS
takeoffs factor)
----------------------------------------------------------------------------------------------------------------
Yokes installed on any Model All Operations... All............. 120 1 120
204B, 205A, or 205A-1
helicopter.
Yokes installed on any Model External Load 1 to 5.......... 105 1 105
205B or 212 helicopter. Operations \1\.
5.1 to 8........ ........... 1.5 .................
8.1 to 12....... ........... 2 .................
12.1 to 18...... ........... 3 .................
18.1 to 32...... 170 5 850
32.1 to 48...... ........... 7 .................
48.1 or above... ........... 9 .................
Unknown......... 50 7 350

[[Page 67631]]

Internal Load All Takeoffs.... 2,025 1 2,025
Operations.
---------------------------------------------------------------------------------
Total Factored Hours TIS ................. ................ ........... ........... 3,450
on Yoke (Summation of the
Factored Hours TIS).
----------------------------------------------------------------------------------------------------------------
\1\ For the purposes of this AD, an external load operation occurs each time a helicopter picks up an external
load and drops it off. Any external load lift in which the helicopter achieves a vertical altitude difference
of greater than 200 feet indicated attitude between the pick-up and drop-off point counts as two external load
lifts in determining the proper rate per hour category.

Note 1: The number of unfactored hours TIS and factored hours
TIS contained in Table 1 of this AD are examples and presented for
illustration purposes only.

(4) By reference to Table 1 of this AD, enter the ``Unfactored
Hours TIS'' for each category as determined by paragraph (a)(3) of
this AD. Calculate the ``Factored Hours TIS'' by multiplying the
``Unfactored Hours TIS'' by the ``Hours TIS Factor.'' Determine the
accumulated ``Total Factored Hours TIS'' on each yoke by adding the
factored hours TIS for each type of operation and helicopter model.
Tracking the Total Factored Hours TIS is only for establishing a
retirement life and not for tracking inspection intervals.
(5) Record the accumulated Total Factored Hours TIS on the
component history card or equivalent record for each yoke.
(6) Continue to factor the hours TIS for each yoke by following
paragraph (a)(2) through (a)(4) of this AD, and record the
additional factored hours TIS on the component history card or
equivalent record.
(b) For helicopters with yoke, P/N 204-011-102 (all dash
numbers), installed, before further flight, unless accomplished
previously:
(1) For hours TIS accumulated before the effective date of this
AD, calculate and record the Total Factored Hours TIS as follows:
(i) For the Model 212 helicopters, 1 hour TIS in which passenger
or internal cargo was carried equals 1 factored hour TIS; 1 hour TIS
where more than 4 external load lifts occurred equals 5 factored
hours TIS.
(ii) For the Model 204 and 205 series helicopters, 1 hour TIS
equals 1 factored hour TIS.

Note 2: Paragraph (b)(1) gives credit to the operators for
compliance with ADs 81-19-01 and 81-19-02 in establishing the
starting point for the new factoring of hours TIS contained in this
AD.

Note 3: The accumulated Total Factored Hours TIS for yoke, P/N
204-011-102 (all dash numbers), calculated in accordance with the
applicable Bell Model 204B, 205A-1, 205B, or 212 maintenance
manuals, which results in an equal or higher accumulated Total
Factored Hours TIS is an acceptable alternative to meeting the
factoring requirements of AD 81-19-01 (contained in Bell ASB 212-81-
23, dated June 22, 1981, for the Model 212 helicopters) and AD 81-
19-02 (contained in Bell ASBs 204-81-11 and 205-81-16, both dated
June 22, 1981, for the Model 204 and 205 series helicopters).

(2) For hours TIS accumulated after the effective date of this
AD, calculate and record the factored hours TIS on the yoke in
accordance with the requirements of paragraphs (a)(1) thorough
(a)(6) of this AD.
(c) Revise the Airworthiness Limitations section of the
applicable maintenance manuals or the Instructions for Continued
Airworthiness (ICAs) by establishing a new retirement life of 3,600
Total Factored Hours TIS for each yoke, P/N AAI-4011-102 (all dash
numbers), ASI-4011-102 (all dash numbers), or 204-011-102 (all dash
numbers), by making pen and ink changes or inserting a copy of this
AD into the Airworthiness Limitations section of the maintenance
manual or ICAs.
(d) Unless accomplished previously, record a life limit of 3,600
Total Factored Hours TIS for each yoke, P/N AAI-4011-102 (all dash
numbers), ASI-4011-102 (all dash numbers), or 204-011-102 (all dash
numbers), on the component history card or equivalent record.
(e) Within 100 hours TIS or 600 hours TIS since the last
magnetic particle inspection (MPI) of the yoke, whichever occurs
later, and thereafter at intervals not to exceed 600 hours TIS, for
any yoke installed on any Model 205B or 212 helicopter:
(1) Remove the yoke from the main rotor hub assembly (hub).
Using a 5-power or higher magnifying glass, visually inspect each
pillow block bushing hole, spindle radius, and center section web
for any corrosion or mechanical damage.
(2) Perform an MPI of each yoke for a crack.

Note 4: MPI procedures are contained in Bell Standard Practices
Manual BHT-ALL-SPM.

(f) Within 100 hours TIS or 2,400 hours TIS since the last MPI
of the yoke, whichever occurs later, and thereafter at intervals not
to exceed 2,400 hours TIS, for any yoke installed on any Model 204B,
205A, or 205A-1 helicopter:
(1) Remove the yoke from the hub. Using a 5-power or higher
magnifying glass, visually inspect each pillow block bushing hole,
spindle radius, and center section web for any corrosion or
mechanical damage.
(2) Perform an MPI of each yoke for a crack.
(g) Before further flight, replace each yoke with an airworthy
yoke if:
(1) The yoke has 3,600 or more Total Factored Hours TIS; or
(2) The Total Factored Hours TIS for the yoke is unknown and
cannot be determined; or
(3) The yoke has any corrosion or mechanical damage that exceeds
any of the maximum repair damage limits; or

Note 5: The applicable Bell Component and Repair Overhaul Manual
contains the maximum repair damage limitations.

(4) The yoke has a crack.
(h) 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, Rotorcraft Directorate,
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-
5170, fax (817) 222-5783, for information about previously approved
alternative methods of compliance.
(i) Special flight permits may only be issued under 14 CFR
21.197 and 21.199 for the purpose of operating the helicopter to a
location where the MPI requirements of paragraphs (e) or (f) of this
AD can be performed.
(j) The Joint Aircraft System Component (JASC) Code is 6220:
Main Rotor Head Issued in Fort Worth, Texas, on October 21, 2011.

Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-28361 Filed 11-1-11; 8:45 am]
BILLING CODE 4910-13-P

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