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

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