Airworthiness Directives; Boeing Model 737 Airplanes, 66474-66480 [E6-19227]

Download as PDF 66474 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14300 (70 FR 57732, October 4, 2005) and adding the following new airworthiness directive (AD): required by paragraph (f) of this AD, before further flight, repair the crack according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the DGAC (or its delegated agent); or the EASA (or its delegated agent). DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 New Requirements of This AD [Docket No. FAA–2006–26323; Directorate Identifier 2006–NM–150–AD] Airbus: Docket No. FAA–2006–26324; Directorate Identifier 2006–NM–214–AD. Installation for Model A330–200 and –300 Series Airplanes RIN 2120–AA64 Comments Due Date (a) The FAA must receive comments on this AD action by December 15, 2006. (h) For all airplanes: At the later of the times in paragraphs (h)(1) and (h)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between LH and RH STR13; and do all related investigative and other specified actions before further flight, as applicable. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3143, Revision 01, including Appendix 01, dated June 29, 2006; except if any crack is detected during a related investigative action (rototest), before further flight, repair the crack using a method approved by the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). (1) Before the accumulation of 17,600 total flight cycles or 61,600 total flight hours, whichever occurs earlier. (2) Within 6 months after the effective date of this AD. Affected ADs (b) This AD supersedes AD 2005–20–07. Applicability (c) This AD applies to Airbus Model A330– 201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes, certificated in any category; except those on which Airbus Modification 49202 has been incorporated in production. Unsafe Condition (d) This AD results from cracking found at the circumferential joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2005–20–07 rmajette on PROD1PC67 with PROPOSALS1 Installation for Model A330–300 Series Airplanes (f) For Airbus Model A330–301, –321, –322, –323, –341, –342, and –343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: At the later of the times in paragraphs (f)(1) and (f)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and do all related investigative and corrective actions before further flight. Except as provided by paragraph (g) of this AD, do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3127, Revision 01, dated November 21, 2003. (1) Before the accumulation of 14,700 total flight cycles or 51,400 total flight hours, whichever occurs earlier. (2) Within 6 months after October 19, 2005 (the effective date of AD 2005–20–07). ´ ´ Contact the FAA/Direction Generale de l’Aviation Civile (DGAC)/European Aviation Safety Agency (EASA) for Certain Repair Instructions (g) For Airbus Model A330–301, –321, –322, –323, –341, –342, and –343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: If any crack is detected during the related investigative actions (rototest) VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 Credit for Actions Done in Accordance With Previous Service Bulletin (i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A330–53–3143, including Appendix 01, dated December 24, 2004, are acceptable for compliance with the corresponding requirements of paragraph (h) of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) EASA airworthiness directive 2006– 0266, dated August 30, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on November 7, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–19228 Filed 11–14–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Airworthiness Directives; Boeing Model 737 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Boeing Model 737 airplanes. The existing AD currently requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. For certain airplanes, this proposed AD would add, among other actions, repetitive tests of the force fight monitor of the main rudder power control unit (PCU), repetitive tests of the standby hydraulic actuation system, and corrective action; as applicable. For those airplanes, this proposed AD also would add, among other actions, replacement of both input control rods of the main rudder PCU and the input control rod of the standby rudder PCU with new input control rods, as applicable, which would end the repetitive tests. For certain other airplanes, this proposed AD would add installation of an enhanced rudder control system in accordance with new service information. This proposed AD results from a report of a fractured rod end on an input control rod of the main rudder PCU. We are proposing this AD to prevent failure of one of the two input control rods of main rudder PCU, which, under certain conditions, could result in reduced controllability of the airplane; and to prevent failure of any combination of two input control rods of the main rudder PCU and/or standby rudder PCU, which could result in loss of control of the airplane. We are also proposing this AD to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam. DATES: We must receive comments on this proposed AD by January 2, 2007. E:\FR\FM\15NOP1.SGM 15NOP1 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Kenneth W. Frey, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6468; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: ADDRESSES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–26323; Directorate Identifier 2006–NM–150– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On October 30, 2002, we issued AD 2002–20–07 R1, amendment 39–12940 (67 FR 67518, November 6, 2002), for all Boeing Model 737 airplanes. That AD requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. That AD resulted from FAA determinations that the existing system design architecture is unsafe. We issued that AD to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam. 66475 Actions Since Existing AD Was Issued Since the issuance of AD 2002–20–07 R1, we have received a report of a fractured rod end on one of the two input control rods of the main rudder power control unit (PCU) on a Model 737–800 series airplane. This condition was discovered during heavy maintenance. The rod end had not separated from the input control rod and was retained by the sealant used during the assembly of the input control rod. The condition was discovered because the aft rod end of the lower input control rod appeared loose. If the rod end does not separate from the input control rod, there is no indication of fracture and it will not likely be detected during normal flight operation. If a rod end separates from an input control rod of the main rudder PCU, the input to the A and B sides of the main rudder PCU (the main rudder PCU is a dual tandem actuator) will not match. This condition will cause a force fight between the A and B sides in the main rudder PCU, which will activate the force fight monitor, activate the standby hydraulic system, and illuminate the STBY RUD ON light on the P5–3 panel. Dispatch is not allowed with the STBY RUD ON light illuminated. The incident airplane had been modified to comply with the requirements of AD 2002–20–07 R1. We previously approved the service bulletins in the table titled ‘‘Previously Approved Service Bulletins’’ as an alternative method of compliance (AMOC) for the requirements of AD 2002–20–07 R1. These service bulletins include procedures to replace both input control rods of the main rudder PCU and the input control rod of the standby rudder PCU (for certain airplanes) with new input control rod(s) having part number (P/N) 251A3495–1, which, we have since determined, had an improper heat treatment during manufacture. PREVIOUSLY APPROVED SERVICE BULLETINS For model— Boeing Service Bulletin 737–100, –200, and –200C series airplanes ..... 737–27–1252, Revision 2, dated December 9, 2004; Revision 1, dated September 25, 2003; and Original Issue, dated June 26, 2003. 737–27–1255, Revision 2, dated July 22, 2004; Revision 1, dated June 26, 2003; and Original Issue, dated May 1, 2003. 737–27–1253, Revision 2, dated October 7, 2004; Revision 1, dated March 27, 2003; and Original Issue, dated January 2, 2003. rmajette on PROD1PC67 with PROPOSALS1 737–300, –400, and –500 series airplanes ........ 737–600, –700, –700C, –800, and –900 series airplanes. Failure of one of the two input control rods of the main rudder PCU under certain conditions, if not corrected, VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 could result in reduced controllability of the airplane. Failure of any combination of two input control rods PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 of the main rudder PCU and/or standby rudder PCU, if not corrected, could result in loss of control of the airplane. E:\FR\FM\15NOP1.SGM 15NOP1 66476 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules Relevant Service Information We have reviewed the service bulletins in the table titled ‘‘Service Bulletins for Repetitive Tests and Other Actions.’’ The service bulletins specify an initial compliance time for doing the initial test of the standby system of within 60 days after the date of the service bulletin, and a repetitive interval of 500 flight hours. The service bulletins also specify an initial compliance time for doing the initial test of the force fight monitor of within 90 days or 6,000 flight hours after the date of the service bulletin, depending on the airplane configuration, and a repetitive interval of 6,000 flight hours. For airplanes identified as Groups 1 and 2, Configuration 2, in Boeing Alert Service Bulletin 737–27A1281, dated June 14, 2006; and airplanes identified as Group 1, Configuration 2, in Boeing Alert Service Bulletin 737–27A1280, dated May 25, 2006; no work is necessary in accordance with these service bulletins. The improperly heat-treated control rods were not installed on those airplanes. SERVICE BULLETINS FOR REPETITIVE TESTS AND OTHER ACTIONS For certain model— Boeing Alert Service Bulletin 737–600, –700, –700C, –800 and –900 series airplanes. 737–27A1280, 2005. dated May 25, 737–100, –200, –200C, –300, –400, and –500 series airplanes. 737–27A1281, 2006. dated June 14, We also have reviewed the service bulletins in the table titled, ‘‘Service Bulletins for Installation of an RSEP and Describes procedures for doing— The ‘‘Rudder Main Power Control Unit Force Fight Monitor Test,’’ the ‘‘Operational Test of the Standby Hydraulic Actuation System,’’ and applicable corrective action if necessary. The ‘‘Rudder Main Power Control Unit Force Fight Test,’’ the ‘‘Standby Rudder Actuator Shutoff Valve Test,’’ and applicable corrective action if necessary. Replacement of Input control rods.’’ Boeing uses the acronym RSEP for the ‘‘Rudder System Enhancement Program.’’ SERVICE BULLETINS FOR INSTALLATION OF AN RSEP AND REPLACEMENT OF INPUT CONTROL RODS Which ends the repetitive tests specified in Boeing Service Bulletin— For certain model— Boeing— Describes procedures for— 737–100, –200, and –200C series airplanes. Service Bulletin 737–27– 1252, Revision 3, dated May 12, 2006. Service Bulletin 737–27– 1255, Revision 3, dated May 10, 2006. Service Bulletin 737–27– 1253, Revision 3, dated May 12, 2006. Installing an RSEP (Part 1), and replacing both input control rods of the main rudder PCU with new input control rods (Part 2). Installing an RSEP (Part 1), and replacing both input control rods of the main rudder PCU with new input control rods (Part 2). Installing an RSEP (Part 1); and replacing both input control rods of the main rudder PCU with new input control rods, inspecting the control rod of the standby rudder PCU to determine if part number (P/N) 251A3495–1 is installed, and doing corrective action if necessary (Part 2) (i.e., replacing any improperly heat-treated input control rod with a new input control rod). Replacing both input control rods of the main rudder PCU and the input control rod of the standby rudder PCU with new input control rod(s). 737–300, –400, and –500 series airplanes. 737–600, –700, –700C, –800, and –900 series airplanes. Alert Service Bulletin 737– 27A1279, dated June 20, 2006. Boeing Alert Service Bulletins 737– 27–1252, 737–27–1253, and 737–27– 1255, all Revision 3, also specify prior or concurrent accomplishment of the 737–27A1281, dated June 14, 2006. 737–27A1281, dated June 14, 2006. 737–27A1280, dated May 25, 2005. 737–27A1280, dated May 25, 2005. actions described in the table titled, ‘‘Prior/Concurrent Service Information.’’ PRIOR/CONCURRENT SERVICE INFORMATION Do this action— In accordance with— 737–27–1252, Revision 3, dated May 12, 2006. rmajette on PROD1PC67 with PROPOSALS1 Prior to or concurrently with the actions in Boeing Alert Service Bulletin— Remove the rudder position sensor of the automatic flight control system. Replace the rudder feel and centering assembly with a new all-mechanical unit. Install the rudder pressure reducer and yaw damper coupler. Install provisional wires for rudder system enhancement. Replace the P5–3 panel with a new panel. Boeing Service Bulletin 737–22–1042, Revision 1, dated April 5, 1985. Boeing Service Bulletin 737–27–1026, dated January 15, 1971. VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Boeing Service Bulletin 737–27A1206, Revision 3, dated December 14, 2000. Boeing Service Bulletin 737–27–1246, Revision 1, dated February 21, 2002. Boeing Service Bulletin 737–27–1263, Revision 1, dated September 25, 2003. E:\FR\FM\15NOP1.SGM 15NOP1 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules 66477 PRIOR/CONCURRENT SERVICE INFORMATION—Continued Prior to or concurrently with the actions in Boeing Alert Service Bulletin— 737–27–1253, Revision 3, dated May 12, 2006. 737–27–1255, Revision 3, dated May 10, 2006. Do this action— In accordance with— Replace the input lever for the auxiliary rudder power control package with a new input lever. Install provisional wires for rudder system enhancement. Replace the P5–3 panel with a new panel. Relocate the wire bundle routing in the vertical stabilizer. Install provisional wires for rudder system enhancement. Replace the P5–3 panel with a new panel. Install a new yaw damper coupler ........ Smiths Aerospace Service Bulletin 1150–27–05A, dated August 28, 2003. Inspect and rework the trailing edge beam on the vertical fin. Replace the input lever for the auxiliary rudder power control package with a new input lever. Boeing Service Bulletin 737–27–1247, Revision 1, dated July 25, 2002. Boeing Service Bulletin 737–27–1262, dated December 19, 2002. Boeing Alert Service Bulletin 737–27A1239, dated January 11, 2001. Boeing Service Bulletin 737–27–1246, Revision 1, dated February 21, 2002. Boeing Service Bulletin 737–27–1265, Revision 1, dated April 3, 2003. Boeing Service Bulletin 737–27A1206, Revision 3, dated December 14, 2000. Boeing Service Bulletin 737–55–1052, Revision 1, dated August 5, 2004. Smiths Aerospace Service Bulletin 1150–27–05A, dated August 28, 2003. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. require suspending a certain Master Minimum Equipment Item, until the improperly heat-treated input control rods are replaced. FAA’s Determination and Requirements of the Proposed AD Change to Existing AD We have evaluated all pertinent information and identified an unsafe condition that is likely to develop on other airplanes of the same type design. For this reason, we are proposing this AD, which would supersede AD 2002– 20–07 R1 and would retain the requirements of the existing AD. This proposed AD would also require accomplishing the actions specified in the applicable service information described previously. For certain airplanes, this proposed AD also would This proposed AD would retain all requirements of AD 2002–20–07 R1. Since AD 2002–20–07 R1 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Corresponding requirement in this proposed AD Requirement in AD 2002–20–07 R1 paragraph (a) ............ paragraph (b) ............ paragraph (f). paragraph (b) (with new title). Costs of Compliance There are about 6,412 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 1,678 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate is $80 per work hour. ESTIMATED COSTS Work hours Action Parts Cost per airplane Fleet cost 700 $140,000 ......................... $196,000 ................... $328,888,000. 2 None ............................... $160, per test cycle ... Replacement of the input control rods (new action proposed by this NPRM) (ends repetitive tests). rmajette on PROD1PC67 with PROPOSALS1 Installation of rudder control system (required by AD 2002–20–07 R1, and retained in this NPRM). Repetitive tests, per test cycle (new action proposed by this NPRM). 5 to 7 The manufacturer states that it will supply required parts to the operators at no cost. $400 to $560 ............. Up to $268,480 depending on the configuration of the airplanes. Up to $939,680, depending the configuration of the airplanes. 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 VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 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 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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 E:\FR\FM\15NOP1.SGM 15NOP1 66478 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules adding the following new airworthiness directive (AD): that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the National Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–12940 (67 FR 67518, November 6, 2002) and Compliance Boeing: Docket No. FAA–2006–26323; Directorate Identifier 2006–NM–150–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 2, 2007. (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2002–20–07 R1 Affected ADs (b) This AD affects the ADs specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD. (1) This AD supersedes AD 2002–20–07 R1. (2) For airplanes on which the actions required by paragraph (f) of this AD have been done before the effective date of this AD: Doing the actions in paragraph (f) of this AD ends the requirements of the ADs listed in Table 1 of this AD. (3) For airplanes on which the actions required by paragraph (f) of this AD have not been done before the effective date of this AD: Doing the actions in paragraph (h) of this AD ends the requirements of the ADs listed in Table 1 of this AD. TABLE 1.—OTHER ADS AD Amendment 97–09–15 R1 ........................ 99–11–05 .............................. 2000–22–02 R1 .................... 39–10912 39–11175 39–11948 Applicability (c) This AD applies to all Boeing Model 737–100, –200, –200C, –300, –400, –500, –600, –700,–700C, –800 and –900 series airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report of a fractured rod end on an input control rod of the main rudder power control unit (PCU). We are issuing this AD to prevent failure of one of the two input control rods of the main rudder PCU, which, under certain conditions, could result in reduced controllability of the airplane; and to prevent failure of any combination of two input control rods of the main rudder PCU and/or standby rudder PCU, which could result in loss of control of the airplane. We are also issuing this AD to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam. Installation (f) Except as provided by paragraphs (h) and (i) of this AD: Within 6 years after November 12, 2002 (the effective date of AD 2002–20–07), do the actions required by paragraphs (f)(1) and (f)(2) of this AD, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. (1) Install a new rudder control system that includes new components such as an aft torque tube, hydraulic actuators, and associated input control rods, and additional wiring throughout the airplane to support failure annunciation of the rudder control system in the flight deck. The system also must incorporate two separate inputs, each with an override mechanism, to two separate servo valves on the main rudder PCU; and an input to the standby PCU that also will include an override mechanism. (2) Make applicable changes to the adjacent systems to accommodate the new rudder control system. New Requirements of This AD For Certain Airplanes: Tests, Suspension of Certain Master Minimum Equipment Item, Replacements, Inspection, and Corrective Actions (g) For airplanes on which the actions required by paragraph (f) of this AD have been done before the effective date of this AD: Do the actions in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as applicable. (1) At the applicable times listed in paragraph 1.E., ‘‘Compliance,’’ of the applicable service bulletin specified in Table 2 of this AD; except, where the service bulletin specifies a compliance time from the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD: Do the tests specified in Table 2 of this AD, until the installation required by paragraph (g)(3) of this AD has been done in accordance with the applicable service bulletin in Table 3 of this AD. Do all applicable corrective actions specified in Table 2 of this AD before further flight. TABLE 2.—REPETITIVE TESTS In accordance with the accomplishment instructions of— rmajette on PROD1PC67 with PROPOSALS1 For model— Identified as— Do— (i) 737–100, –200, and –200C series airplanes. Group 1, Configuration 1 in the service bulletin. The ‘‘Rudder Main Power Control Unit Force Fight Test,’’ the ‘‘Standby Rudder Actuator Shutoff Valve Test,’’ and any applicable corrective action. (ii) 737–300, –400, and –500 series airplanes. Group 2, Configuration 1 in the service bulletin. The ‘‘Rudder Main Power Control Unit Force Fight Test,’’ the ‘‘Standby Rudder Actuator Shutoff Valve Test,’’ and any applicable corrective action. VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 E:\FR\FM\15NOP1.SGM 15NOP1 Boeing Alert Service Bulletin 737– 27A1281, dated June 14, 2006. Boeing Alert Service Bulletin 737– 27A1281, dated June 14, 2006. Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules 66479 TABLE 2.—REPETITIVE TESTS—Continued For model— Identified as— Do— In accordance with the accomplishment instructions of— (iii) 737–600, –700, –700C, –800, and –900 series airplanes. Group 1, Configuration 1 and Group 2, Configurations 1 and 2 in the service bulletin. The ‘‘Rudder Main Power Control Unit Force Fight Monitor Test,’’ the ‘‘Operational Test of the Standby Hydraulic Actuation System,’’ and any applicable corrective action. Boeing Alert Service Bulletin 737– 27A1280, dated May 25, 2005. (2) As of the effective date of this AD, do not use the Master Minimum Equipment Item 27–21, ‘‘STBY RUD ON light,’’ until the actions required by paragraph (g)(3) of this AD are done. (3) Within 24 months after the effective date of this AD, do the replacement(s) and inspection, as applicable, specified in Table 3 of this AD. Do all applicable corrective actions specified in Table 3 of this AD before further flight. Doing the applicable action(s) ends the requirements of paragraphs (g)(1) and (g)(2) of this AD. TABLE 3.—REPLACEMENT OF INPUT CONTROL RODS, INSPECTION, AND CORRECTIVE ACTION, AS APPLICABLE For Model— Identified as— (i) 737–100, –200, and –200C series airplanes. (ii) 737–300, –400, and –500 series airplanes. (iii) 737–600, –700, –700C, –800, and –900 series airplanes. Groups 1 through 9, Configuration 3 in the service bulletin. (iv) 737–600, –700, –700C, –800, and –900 series airplanes. Do the following action(s)— In accordance with— Replace both input control rods of the main rudder PCU with new input control rods. Groups 1 through 19, Configu- Replace both input control rods of the ration 3 in the service bulletin. main rudder PCU with new input control rods. Groups 1 through 20, Configu- Replace both input control rods of the ration 3 in the service bulletin. main rudder PCU with new input control rods, inspect the input control rod of the standby rudder PCU to determine if part number (P/N) 251A3495–1 is installed, and any corrective action. Group 1 in the service bulletin Replace both input control rods of the main rudder PCU and the input control rod of the standby rudder PCU with a new input control rod(s). For Certain Other Airplanes: Install New Rudder Control System per Service Information (h) For airplanes on which the actions required by paragraph (f) of this AD have not been done before the effective date of this AD: As of the effective date of this AD, use the applicable service bulletin specified in Table 4 of this AD to do the actions required Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 737–27– 1252, Revision 3, dated May 12, 2006. Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 737–27– 1255, Revision 3, dated May 10, 2006. Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 737–27– 1253, Revision 3, dated May 12, 2006. The Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1279, dated June 20, 2006. by paragraph (f) of this AD at the time specified in that paragraph. TABLE 4.—SERVICE BULLETINS FOR INSTALLATION OF NEW RUDDER CONTROL SYSTEM For model— Identified as— Do the actions required by paragraph (f) of this AD in accordance with— (1) 737–100, –200, and –200C series airplanes. Groups 1 through 9, Configurations 1 and 2 in the service bulletin. Groups 1 through 19, Configurations 1 and 2 in the service bulletin. Groups 1 through 20, Configurations 1 and 2 in the service bulletin. Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 737–27–1252, Revision 3, dated May 12, 2006. (2) 737–300, –400, and –500 series airplanes. (3) 737–600, –700, –700C, –800, and –900 series airplanes. Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 737–27–1255, Revision 3, dated May 10, 2006. Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 737–27–1253, Revision 3, dated May 12, 2006. rmajette on PROD1PC67 with PROPOSALS1 (i) Before or concurrently with the requirements of paragraph (h) of this AD, do the actions in Table 5 of this AD. VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\15NOP1.SGM 15NOP1 66480 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules TABLE 5.—BEFORE/CONCURRENT REQUIREMENTS Before or concurrently with the actions specified in— Do these actions— In accordance with the accomplishment instructions of— (1) Paragraph (h)(1) of this AD .......................... (i) Remove the rudder position sensor of the automatic flight control system. (ii) Replace the rudder feel and centering assembly with a new all-mechanical unit. (iii) Install the rudder pressure reducer and yaw damper coupler. (iv) Install provisional wires for rudder system enhancement. (v) Replace the P5–3 panel with a new panel Boeing Service Bulletin 737–22–1042, Revision 1, dated April 5, 1985. Boeing 737 Service Bulletin 27–1026, dated January 15, 1971. Boeing Service Bulletin 737–27A1206, Revision 3, dated December 14, 2000. Boeing Service Bulletin 737–27–1246, Revision 1, dated February 21, 2002. Boeing Service Bulletin 737–27–1263, Revision 1, dated September 25, 2003. Smiths Aerospace Service Bulletin 1150–27– 05A, dated August 28, 2003. (2) Paragraph (h)(2) of this AD .......................... (vi) Replace the input lever for the auxiliary rudder power control package with a new input lever. (i) Install provisional wires for rudder system enhancement. (ii) Replace the P5–3 panel with a new panel (iii) Install a new yaw damper coupler ............. (3) Paragraph (h)(3) of this AD .......................... (iv) Inspect the trailing edge beam on the vertical fin and rework if necessary. (v) Replace the input lever for the auxiliary rudder power control package with a new input lever. (i) Install provisional wires for rudder system enhancement. (ii) Replace the P5–3 panel with a new panel (iii) Relocate the wire bundle routing in the vertical stabilizer. DEPARTMENT OF TRANSPORTATION (j) As of the effective date of this AD, no person may install an input control rod, P/ N 251A3495–1, on any airplane. National Highway Traffic Safety Administration Alternative Methods of Compliance (AMOCs) 49 CFR Part 571 (k)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) Except as provided by paragraph (j) of this AD: AMOCs approved previously in accordance with AD 2002–20–07 R1 are approved as AMOCs for the corresponding provisions of paragraphs (f) and (h) of this AD. rmajette on PROD1PC67 with PROPOSALS1 Parts Installation [Docket No. NHTSA–2006–26299] Issued in Renton, Washington, on November 3, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–19227 Filed 11–14–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 Federal Motor Vehicle Safety Standards; Brake Hoses National Highway Traffic Safety Administration (NHTSA), Department of Transportation. ACTION: Notice of proposed rulemaking; proposed delay of effective date. AGENCY: SUMMARY: NHTSA published a final rule in December 2004 that amended the Federal motor vehicle safety standard on brake hoses. In early 2005, the agency received several petitions for reconsideration of the rule and a petition to delay the effective date of the final rule. At present, the rule is to take effect on December 20, 2006. To allow for more time to respond to petitions for reconsideration, and to give industry more time to meet new requirements, this document proposes to delay the effective date of the final rule for one year, to December 20, 2007. DATES: You should submit your comments not later than November 30, 2006. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Boeing Service Bulletin 737–27–1246, Revision 1, dated February 21, 2002. Boeing Service Bulletin 737–27–1264, Revision 1, dated April 3, 2003. Boeing Service Bulletin 737–27A1206, Revision 3, dated December 14, 2000. Boeing Service Bulletin 737–55–1052, Revision 1, dated August 5, 2004. Smiths Aerospace Service Bulletin 1150–27– 05A, dated August 28, 2003. Boeing Service Bulletin 737–27–1247, Revision 1, dated July 25, 2002. Boeing Service Bulletin 737–27–1262, dated December 19, 2002. Boeing Alert Service Bulletin 737–27A1239, dated January 11, 2001. We invite you to submit comments on the proposed delay of the effective date of the final rule published on December 20, 2004. You may submit comments identified by docket number at the heading of this notice by any of the following methods: • Web Site: https://dms.dot.gov. Follow the instructions for submitting comments on the DOT electronic docket site by clicking on ‘‘Help and Information’’ or ‘‘Help/Info.’’ • Fax: 1–(202)–493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the online instructions for submitting comments. Instructions: All submissions must include the agency name and docket number. Note that all comments received will be posted without change to https://dms.dot.gov, including any personal information provided. Docket: For access to the docket in order to read background documents or comments received, go to https:// ADDRESSES: E:\FR\FM\15NOP1.SGM 15NOP1

Agencies

[Federal Register Volume 71, Number 220 (Wednesday, November 15, 2006)]
[Proposed Rules]
[Pages 66474-66480]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19227]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26323; Directorate Identifier 2006-NM-150-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Boeing Model 737 airplanes. The 
existing AD currently requires installation of a new rudder control 
system and changes to the adjacent systems to accommodate that new 
rudder control system. For certain airplanes, this proposed AD would 
add, among other actions, repetitive tests of the force fight monitor 
of the main rudder power control unit (PCU), repetitive tests of the 
standby hydraulic actuation system, and corrective action; as 
applicable. For those airplanes, this proposed AD also would add, among 
other actions, replacement of both input control rods of the main 
rudder PCU and the input control rod of the standby rudder PCU with new 
input control rods, as applicable, which would end the repetitive 
tests. For certain other airplanes, this proposed AD would add 
installation of an enhanced rudder control system in accordance with 
new service information. This proposed AD results from a report of a 
fractured rod end on an input control rod of the main rudder PCU. We 
are proposing this AD to prevent failure of one of the two input 
control rods of main rudder PCU, which, under certain conditions, could 
result in reduced controllability of the airplane; and to prevent 
failure of any combination of two input control rods of the main rudder 
PCU and/or standby rudder PCU, which could result in loss of control of 
the airplane. We are also proposing this AD to prevent an uncommanded 
rudder hardover event and consequent loss of control of the airplane 
due to inherent failure modes, including single-jam modes, and certain 
latent failures or jams combined with a second failure or jam.

DATES: We must receive comments on this proposed AD by January 2, 2007.

[[Page 66475]]


ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Kenneth W. Frey, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6468; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-26323; Directorate Identifier 2006-NM-150-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or may 
visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On October 30, 2002, we issued AD 2002-20-07 R1, amendment 39-12940 
(67 FR 67518, November 6, 2002), for all Boeing Model 737 airplanes. 
That AD requires installation of a new rudder control system and 
changes to the adjacent systems to accommodate that new rudder control 
system. That AD resulted from FAA determinations that the existing 
system design architecture is unsafe. We issued that AD to prevent an 
uncommanded rudder hardover event and consequent loss of control of the 
airplane due to inherent failure modes, including single-jam modes, and 
certain latent failures or jams combined with a second failure or jam.

Actions Since Existing AD Was Issued

    Since the issuance of AD 2002-20-07 R1, we have received a report 
of a fractured rod end on one of the two input control rods of the main 
rudder power control unit (PCU) on a Model 737-800 series airplane. 
This condition was discovered during heavy maintenance. The rod end had 
not separated from the input control rod and was retained by the 
sealant used during the assembly of the input control rod. The 
condition was discovered because the aft rod end of the lower input 
control rod appeared loose. If the rod end does not separate from the 
input control rod, there is no indication of fracture and it will not 
likely be detected during normal flight operation.
    If a rod end separates from an input control rod of the main rudder 
PCU, the input to the A and B sides of the main rudder PCU (the main 
rudder PCU is a dual tandem actuator) will not match. This condition 
will cause a force fight between the A and B sides in the main rudder 
PCU, which will activate the force fight monitor, activate the standby 
hydraulic system, and illuminate the STBY RUD ON light on the P5-3 
panel. Dispatch is not allowed with the STBY RUD ON light illuminated.
    The incident airplane had been modified to comply with the 
requirements of AD 2002-20-07 R1. We previously approved the service 
bulletins in the table titled ``Previously Approved Service Bulletins'' 
as an alternative method of compliance (AMOC) for the requirements of 
AD 2002-20-07 R1. These service bulletins include procedures to replace 
both input control rods of the main rudder PCU and the input control 
rod of the standby rudder PCU (for certain airplanes) with new input 
control rod(s) having part number (P/N) 251A3495-1, which, we have 
since determined, had an improper heat treatment during manufacture.

                  Previously Approved Service Bulletins
------------------------------------------------------------------------
         For model--                    Boeing Service Bulletin
------------------------------------------------------------------------
737-100, -200, and -200C       737-27-1252, Revision 2, dated December
 series airplanes.              9, 2004; Revision 1, dated September 25,
                                2003; and Original Issue, dated June 26,
                                2003.
737-300, -400, and -500        737-27-1255, Revision 2, dated July 22,
 series airplanes.              2004; Revision 1, dated June 26, 2003;
                                and Original Issue, dated May 1, 2003.
737-600, -700, -700C, -800,    737-27-1253, Revision 2, dated October 7,
 and -900 series airplanes.     2004; Revision 1, dated March 27, 2003;
                                and Original Issue, dated January 2,
                                2003.
------------------------------------------------------------------------

    Failure of one of the two input control rods of the main rudder PCU 
under certain conditions, if not corrected, could result in reduced 
controllability of the airplane. Failure of any combination of two 
input control rods of the main rudder PCU and/or standby rudder PCU, if 
not corrected, could result in loss of control of the airplane.

[[Page 66476]]

Relevant Service Information

    We have reviewed the service bulletins in the table titled 
``Service Bulletins for Repetitive Tests and Other Actions.'' The 
service bulletins specify an initial compliance time for doing the 
initial test of the standby system of within 60 days after the date of 
the service bulletin, and a repetitive interval of 500 flight hours. 
The service bulletins also specify an initial compliance time for doing 
the initial test of the force fight monitor of within 90 days or 6,000 
flight hours after the date of the service bulletin, depending on the 
airplane configuration, and a repetitive interval of 6,000 flight 
hours. For airplanes identified as Groups 1 and 2, Configuration 2, in 
Boeing Alert Service Bulletin 737-27A1281, dated June 14, 2006; and 
airplanes identified as Group 1, Configuration 2, in Boeing Alert 
Service Bulletin 737-27A1280, dated May 25, 2006; no work is necessary 
in accordance with these service bulletins. The improperly heat-treated 
control rods were not installed on those airplanes.

        Service Bulletins for Repetitive Tests and Other Actions
------------------------------------------------------------------------
                                   Boeing Alert     Describes procedures
      For certain model--        Service Bulletin       for doing--
------------------------------------------------------------------------
737-600, -700, -700C, -800 and  737-27A1280,       The ``Rudder Main
 -900 series airplanes.          dated May 25,      Power Control Unit
                                 2005.              Force Fight Monitor
                                                    Test,'' the
                                                    ``Operational Test
                                                    of the Standby
                                                    Hydraulic Actuation
                                                    System,'' and
                                                    applicable
                                                    corrective action if
                                                    necessary.
737-100, -200, -200C, -300, -   737-27A1281,       The ``Rudder Main
 400, and -500 series            dated June 14,     Power Control Unit
 airplanes.                      2006.              Force Fight Test,''
                                                    the ``Standby Rudder
                                                    Actuator Shutoff
                                                    Valve Test,'' and
                                                    applicable
                                                    corrective action if
                                                    necessary.
------------------------------------------------------------------------

    We also have reviewed the service bulletins in the table titled, 
``Service Bulletins for Installation of an RSEP and Replacement of 
Input control rods.'' Boeing uses the acronym RSEP for the ``Rudder 
System Enhancement Program.''

               Service Bulletins for Installation of an RSEP and Replacement of Input Control Rods
----------------------------------------------------------------------------------------------------------------
                                                                                              Which ends the
                                                                                             repetitive tests
        For certain model--                 Boeing--          Describes procedures for--    specified in Boeing
                                                                                            Service Bulletin--
----------------------------------------------------------------------------------------------------------------
737-100, -200, and -200C series      Service Bulletin 737-   Installing an RSEP (Part     737-27A1281, dated
 airplanes.                           27-1252, Revision 3,    1), and replacing both       June 14, 2006.
                                      dated May 12, 2006.     input control rods of the
                                                              main rudder PCU with new
                                                              input control rods (Part
                                                              2).
737-300, -400, and -500 series       Service Bulletin 737-   Installing an RSEP (Part     737-27A1281, dated
 airplanes.                           27-1255, Revision 3,    1), and replacing both       June 14, 2006.
                                      dated May 10, 2006.     input control rods of the
                                                              main rudder PCU with new
                                                              input control rods (Part
                                                              2).
737-600, -700, -700C, -800, and -    Service Bulletin 737-   Installing an RSEP (Part     737-27A1280, dated May
 900 series airplanes.                27-1253, Revision 3,    1); and replacing both       25, 2005.
                                      dated May 12, 2006.     input control rods of the
                                                              main rudder PCU with new
                                                              input control rods,
                                                              inspecting the control rod
                                                              of the standby rudder PCU
                                                              to determine if part
                                                              number (P/N) 251A3495-1 is
                                                              installed, and doing
                                                              corrective action if
                                                              necessary (Part 2) (i.e.,
                                                              replacing any improperly
                                                              heat-treated input control
                                                              rod with a new input
                                                              control rod).
                                     Alert Service Bulletin  Replacing both input         737-27A1280, dated May
                                      737-27A1279, dated      control rods of the main     25, 2005.
                                      June 20, 2006.          rudder PCU and the input
                                                              control rod of the standby
                                                              rudder PCU with new input
                                                              control rod(s).
----------------------------------------------------------------------------------------------------------------

    Boeing Alert Service Bulletins 737-27-1252, 737-27-1253, and 737-
27-1255, all Revision 3, also specify prior or concurrent 
accomplishment of the actions described in the table titled, ``Prior/
Concurrent Service Information.''

                                      Prior/Concurrent Service Information
----------------------------------------------------------------------------------------------------------------
   Prior to or concurrently with the
    actions in Boeing Alert Service            Do this action--                   In accordance with--
              Bulletin--
----------------------------------------------------------------------------------------------------------------
737-27-1252, Revision 3, dated May 12,  Remove the rudder position      Boeing Service Bulletin 737-22-1042,
 2006.                                   sensor of the automatic         Revision 1, dated April 5, 1985.
                                         flight control system.
                                        Replace the rudder feel and     Boeing Service Bulletin 737-27-1026,
                                         centering assembly with a new   dated January 15, 1971.
                                         all-mechanical unit.
                                        Install the rudder pressure     Boeing Service Bulletin 737-27A1206,
                                         reducer and yaw damper          Revision 3, dated December 14, 2000.
                                         coupler.
                                        Install provisional wires for   Boeing Service Bulletin 737-27-1246,
                                         rudder system enhancement.      Revision 1, dated February 21, 2002.
                                        Replace the P5-3 panel with a   Boeing Service Bulletin 737-27-1263,
                                         new panel.                      Revision 1, dated September 25, 2003.

[[Page 66477]]

 
                                        Replace the input lever for     Smiths Aerospace Service Bulletin 1150-
                                         the auxiliary rudder power      27-05A, dated August 28, 2003.
                                         control package with a new
                                         input lever.
737-27-1253, Revision 3, dated May 12,  Install provisional wires for   Boeing Service Bulletin 737-27-1247,
 2006.                                   rudder system enhancement.      Revision 1, dated July 25, 2002.
                                        Replace the P5-3 panel with a   Boeing Service Bulletin 737-27-1262,
                                         new panel.                      dated December 19, 2002.
                                        Relocate the wire bundle        Boeing Alert Service Bulletin 737-
                                         routing in the vertical         27A1239, dated January 11, 2001.
                                         stabilizer.
737-27-1255, Revision 3, dated May 10,  Install provisional wires for   Boeing Service Bulletin 737-27-1246,
 2006.                                   rudder system enhancement.      Revision 1, dated February 21, 2002.
                                        Replace the P5-3 panel with a   Boeing Service Bulletin 737-27-1265,
                                         new panel.                      Revision 1, dated April 3, 2003.
                                        Install a new yaw damper        Boeing Service Bulletin 737-27A1206,
                                         coupler.                        Revision 3, dated December 14, 2000.
                                        Inspect and rework the          Boeing Service Bulletin 737-55-1052,
                                         trailing edge beam on the       Revision 1, dated August 5, 2004.
                                         vertical fin.
                                        Replace the input lever for     Smiths Aerospace Service Bulletin 1150-
                                         the auxiliary rudder power      27-05A, dated August 28, 2003.
                                         control package with a new
                                         input lever.
----------------------------------------------------------------------------------------------------------------

    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2002-20-07 R1 and would retain the requirements of 
the existing AD. This proposed AD would also require accomplishing the 
actions specified in the applicable service information described 
previously. For certain airplanes, this proposed AD also would require 
suspending a certain Master Minimum Equipment Item, until the 
improperly heat-treated input control rods are replaced.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2002-20-07 R1. 
Since AD 2002-20-07 R1 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
      Requirement in AD 2002-20-07 R1            in this proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (b) (with new
                                             title).
------------------------------------------------------------------------

Costs of Compliance

    There are about 6,412 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 1,678 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The average labor rate 
is $80 per work hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                    Work
             Action                hours           Parts              Cost per airplane            Fleet cost
----------------------------------------------------------------------------------------------------------------
Installation of rudder control         700  $140,000..........  $196,000.....................  $328,888,000.
 system (required by AD 2002-20-
 07 R1, and retained in this
 NPRM).
Repetitive tests, per test               2  None..............  $160, per test cycle.........  Up to $268,480
 cycle (new action proposed by                                                                  depending on the
 this NPRM).                                                                                    configuration of
                                                                                                the airplanes.
Replacement of the input            5 to 7  The manufacturer    $400 to $560.................  Up to $939,680,
 control rods (new action                    states that it                                     depending the
 proposed by this NPRM) (ends                will supply                                        configuration of
 repetitive tests).                          required parts to                                  the airplanes.
                                             the operators at
                                             no cost.
----------------------------------------------------------------------------------------------------------------

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

[[Page 66478]]

that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-12940 (67 FR 67518, November 6, 2002) and adding 
the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2006-26323; Directorate Identifier 2006-NM-
150-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
2, 2007.

Affected ADs

    (b) This AD affects the ADs specified in paragraphs (b)(1), 
(b)(2), and (b)(3) of this AD.
    (1) This AD supersedes AD 2002-20-07 R1.
    (2) For airplanes on which the actions required by paragraph (f) 
of this AD have been done before the effective date of this AD: 
Doing the actions in paragraph (f) of this AD ends the requirements 
of the ADs listed in Table 1 of this AD.
    (3) For airplanes on which the actions required by paragraph (f) 
of this AD have not been done before the effective date of this AD: 
Doing the actions in paragraph (h) of this AD ends the requirements 
of the ADs listed in Table 1 of this AD.

                           Table 1.--Other ADs
------------------------------------------------------------------------
                           AD                                Amendment
------------------------------------------------------------------------
97-09-15 R1.............................................        39-10912
99-11-05................................................        39-11175
2000-22-02 R1...........................................        39-11948
------------------------------------------------------------------------

Applicability

    (c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, -500, -600, -700,-700C, -800 and -900 series airplanes, 
certificated in any category.

Unsafe Condition

    (d) This AD results from a report of a fractured rod end on an 
input control rod of the main rudder power control unit (PCU). We 
are issuing this AD to prevent failure of one of the two input 
control rods of the main rudder PCU, which, under certain 
conditions, could result in reduced controllability of the airplane; 
and to prevent failure of any combination of two input control rods 
of the main rudder PCU and/or standby rudder PCU, which could result 
in loss of control of the airplane. We are also issuing this AD to 
prevent an uncommanded rudder hardover event and consequent loss of 
control of the airplane due to inherent failure modes, including 
single-jam modes, and certain latent failures or jams combined with 
a second failure or jam.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2002-20-07 R1

Installation

    (f) Except as provided by paragraphs (h) and (i) of this AD: 
Within 6 years after November 12, 2002 (the effective date of AD 
2002-20-07), do the actions required by paragraphs (f)(1) and (f)(2) 
of this AD, in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA.
    (1) Install a new rudder control system that includes new 
components such as an aft torque tube, hydraulic actuators, and 
associated input control rods, and additional wiring throughout the 
airplane to support failure annunciation of the rudder control 
system in the flight deck. The system also must incorporate two 
separate inputs, each with an override mechanism, to two separate 
servo valves on the main rudder PCU; and an input to the standby PCU 
that also will include an override mechanism.
    (2) Make applicable changes to the adjacent systems to 
accommodate the new rudder control system.

New Requirements of This AD

For Certain Airplanes: Tests, Suspension of Certain Master Minimum 
Equipment Item, Replacements, Inspection, and Corrective Actions

    (g) For airplanes on which the actions required by paragraph (f) 
of this AD have been done before the effective date of this AD: Do 
the actions in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as 
applicable.
    (1) At the applicable times listed in paragraph 1.E., 
``Compliance,'' of the applicable service bulletin specified in 
Table 2 of this AD; except, where the service bulletin specifies a 
compliance time from the date on the service bulletin, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD: Do the tests specified in Table 2 of this 
AD, until the installation required by paragraph (g)(3) of this AD 
has been done in accordance with the applicable service bulletin in 
Table 3 of this AD. Do all applicable corrective actions specified 
in Table 2 of this AD before further flight.

                                           Table 2.--Repetitive Tests
----------------------------------------------------------------------------------------------------------------
                                                                                      In accordance with  the
          For model--            Identified as--                Do--                accomplishment  instructions
                                                                                                of--
----------------------------------------------------------------------------------------------------------------
(i) 737-100, -200, and -200C    Group 1,          The ``Rudder Main Power Control  Boeing Alert Service Bulletin
 series airplanes.               Configuration 1   Unit Force Fight Test,'' the     737-27A1281, dated June 14,
                                 in the service    ``Standby Rudder Actuator        2006.
                                 bulletin.         Shutoff Valve Test,'' and any
                                                   applicable corrective action.
(ii) 737-300, -400, and -500    Group 2,          The ``Rudder Main Power Control  Boeing Alert Service Bulletin
 series airplanes.               Configuration 1   Unit Force Fight Test,'' the     737-27A1281, dated June 14,
                                 in the service    ``Standby Rudder Actuator        2006.
                                 bulletin.         Shutoff Valve Test,'' and any
                                                   applicable corrective action.

[[Page 66479]]

 
(iii) 737-600, -700, -700C, -   Group 1,          The ``Rudder Main Power Control  Boeing Alert Service Bulletin
 800, and -900 series            Configuration 1   Unit Force Fight Monitor         737-27A1280, dated May 25,
 airplanes.                      and Group 2,      Test,'' the ``Operational Test   2005.
                                 Configurations    of the Standby Hydraulic
                                 1 and 2 in the    Actuation System,'' and any
                                 service           applicable corrective action.
                                 bulletin.
----------------------------------------------------------------------------------------------------------------

    (2) As of the effective date of this AD, do not use the Master 
Minimum Equipment Item 27-21, ``STBY RUD ON light,'' until the 
actions required by paragraph (g)(3) of this AD are done.
    (3) Within 24 months after the effective date of this AD, do the 
replacement(s) and inspection, as applicable, specified in Table 3 
of this AD. Do all applicable corrective actions specified in Table 
3 of this AD before further flight. Doing the applicable action(s) 
ends the requirements of paragraphs (g)(1) and (g)(2) of this AD.

          Table 3.--Replacement of Input Control Rods, Inspection, and Corrective Action, as Applicable
----------------------------------------------------------------------------------------------------------------
                                                                Do the following
            For Model--                Identified as--             action(s)--            In accordance with--
----------------------------------------------------------------------------------------------------------------
(i) 737-100, -200, and -200C        Groups 1 through 9,    Replace both input control  Part 2 of the
 series airplanes.                   Configuration 3 in     rods of the main rudder     Accomplishment
                                     the service bulletin.  PCU with new input          Instructions of Boeing
                                                            control rods.               Service Bulletin 737-27-
                                                                                        1252, Revision 3, dated
                                                                                        May 12, 2006.
(ii) 737-300, -400, and -500        Groups 1 through 19,   Replace both input control  Part 2 of the
 series airplanes.                   Configuration 3 in     rods of the main rudder     Accomplishment
                                     the service bulletin.  PCU with new input          Instructions of Boeing
                                                            control rods.               Service Bulletin 737-27-
                                                                                        1255, Revision 3, dated
                                                                                        May 10, 2006.
(iii) 737-600, -700, -700C, -800,   Groups 1 through 20,   Replace both input control  Part 2 of the
 and -900 series airplanes.          Configuration 3 in     rods of the main rudder     Accomplishment
                                     the service bulletin.  PCU with new input          Instructions of Boeing
                                                            control rods, inspect the   Service Bulletin 737-27-
                                                            input control rod of the    1253, Revision 3, dated
                                                            standby rudder PCU to       May 12, 2006.
                                                            determine if part number
                                                            (P/N) 251A3495-1 is
                                                            installed, and any
                                                            corrective action.
(iv) 737-600, -700, -700C, -800,    Group 1 in the         Replace both input control  The Accomplishment
 and -900 series airplanes.          service bulletin.      rods of the main rudder     Instructions of Boeing
                                                            PCU and the input control   Alert Service Bulletin
                                                            rod of the standby rudder   737-27A1279, dated June
                                                            PCU with a new input        20, 2006.
                                                            control rod(s).
----------------------------------------------------------------------------------------------------------------

For Certain Other Airplanes: Install New Rudder Control System per 
Service Information

    (h) For airplanes on which the actions required by paragraph (f) 
of this AD have not been done before the effective date of this AD: 
As of the effective date of this AD, use the applicable service 
bulletin specified in Table 4 of this AD to do the actions required 
by paragraph (f) of this AD at the time specified in that paragraph.

   Table 4.--Service Bulletins for Installation of New Rudder Control
                                 System
------------------------------------------------------------------------
                                                       Do the actions
                                                   required by paragraph
          For model--            Identified as--     (f) of this AD in
                                                     accordance with--
------------------------------------------------------------------------
(1) 737-100, -200, and -200C    Groups 1 through   Part 1 of the
 series airplanes.               9,                 Accomplishment
                                 Configurations 1   Instructions of
                                 and 2 in the       Boeing Service
                                 service bulletin.  Bulletin 737-27-
                                                    1252, Revision 3,
                                                    dated May 12, 2006.
(2) 737-300, -400, and -500     Groups 1 through   Part 1 of the
 series airplanes.               19,                Accomplishment
                                 Configurations 1   Instructions of
                                 and 2 in the       Boeing Service
                                 service bulletin.  Bulletin 737-27-
                                                    1255, Revision 3,
                                                    dated May 10, 2006.
(3) 737-600, -700, -700C, -     Groups 1 through   Part 1 of the
 800, and -900 series            20,                Accomplishment
 airplanes.                      Configurations 1   Instructions of
                                 and 2 in the       Boeing Service
                                 service bulletin.  Bulletin 737-27-
                                                    1253, Revision 3,
                                                    dated May 12, 2006.
------------------------------------------------------------------------

    (i) Before or concurrently with the requirements of paragraph 
(h) of this AD, do the actions in Table 5 of this AD.

[[Page 66480]]



                Table 5.--Before/Concurrent Requirements
------------------------------------------------------------------------
                                                     In accordance with
 Before or concurrently with   Do these actions--    the accomplishment
 the actions specified in--                           instructions of--
------------------------------------------------------------------------
(1) Paragraph (h)(1) of this  (i) Remove the        Boeing Service
 AD.                           rudder position       Bulletin 737-22-
                               sensor of the         1042, Revision 1,
                               automatic flight      dated April 5,
                               control system.       1985.
                              (ii) Replace the      Boeing 737 Service
                               rudder feel and       Bulletin 27-1026,
                               centering assembly    dated January 15,
                               with a new all-       1971.
                               mechanical unit.
                              (iii) Install the     Boeing Service
                               rudder pressure       Bulletin 737-
                               reducer and yaw       27A1206, Revision
                               damper coupler.       3, dated December
                                                     14, 2000.
                              (iv) Install          Boeing Service
                               provisional wires     Bulletin 737-27-
                               for rudder system     1246, Revision 1,
                               enhancement.          dated February 21,
                                                     2002.
                              (v) Replace the P5-3  Boeing Service
                               panel with a new      Bulletin 737-27-
                               panel.                1263, Revision 1,
                                                     dated September 25,
                                                     2003.
                              (vi) Replace the      Smiths Aerospace
                               input lever for the   Service Bulletin
                               auxiliary rudder      1150-27-05A, dated
                               power control         August 28, 2003.
                               package with a new
                               input lever.
(2) Paragraph (h)(2) of this  (i) Install           Boeing Service
 AD.                           provisional wires     Bulletin 737-27-
                               for rudder system     1246, Revision 1,
                               enhancement.          dated February 21,
                                                     2002.
                              (ii) Replace the P5-  Boeing Service
                               3 panel with a new    Bulletin 737-27-
                               panel.                1264, Revision 1,
                                                     dated April 3,
                                                     2003.
                              (iii) Install a new   Boeing Service
                               yaw damper coupler.   Bulletin 737-
                                                     27A1206, Revision
                                                     3, dated December
                                                     14, 2000.
                              (iv) Inspect the      Boeing Service
                               trailing edge beam    Bulletin 737-55-
                               on the vertical fin   1052, Revision 1,
                               and rework if         dated August 5,
                               necessary.            2004.
                              (v) Replace the       Smiths Aerospace
                               input lever for the   Service Bulletin
                               auxiliary rudder      1150-27-05A, dated
                               power control         August 28, 2003.
                               package with a new
                               input lever.
(3) Paragraph (h)(3) of this  (i) Install           Boeing Service
 AD.                           provisional wires     Bulletin 737-27-
                               for rudder system     1247, Revision 1,
                               enhancement.          dated July 25,
                                                     2002.
                              (ii) Replace the P5-  Boeing Service
                               3 panel with a new    Bulletin 737-27-
                               panel.                1262, dated
                                                     December 19, 2002.
                              (iii) Relocate the    Boeing Alert Service
                               wire bundle routing   Bulletin 737-
                               in the vertical       27A1239, dated
                               stabilizer.           January 11, 2001.
------------------------------------------------------------------------

Parts Installation

    (j) As of the effective date of this AD, no person may install 
an input control rod, P/N 251A3495-1, on any airplane.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) Except as provided by paragraph (j) of this AD: AMOCs 
approved previously in accordance with AD 2002-20-07 R1 are approved 
as AMOCs for the corresponding provisions of paragraphs (f) and (h) 
of this AD.

    Issued in Renton, Washington, on November 3, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-19227 Filed 11-14-06; 8:45 am]
BILLING CODE 4910-13-P