Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes, 41607-41611 [E9-19180]

Download as PDF Federal Register / Vol. 74, No. 158 / Tuesday, August 18, 2009 / Rules and Regulations FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. cprice-sewell on DSKDVH8Z91PROD with RULES Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007– 0307, dated December 17, 2007; and BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–200, Revision 1, dated March 13, 2007; for related information. Material Incorporated by Reference (i) You must use BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 200, Revision 1, dated March 13, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet https://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the VerDate Nov<24>2008 14:34 Aug 17, 2009 Jkt 217001 availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_ locations.html. Issued in Renton, Washington, on August 4, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–19442 Filed 8–17–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1143; Directorate Identifier 2008–NM–136–AD; Amendment 39–15990; AD 2009–16–07] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–600, –700, –700C, –800, and –900 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737–600, –700, –700C, –800, and –900 series airplanes. That AD currently requires replacing brackets that hold the P5 panel to the airplane structure, the standby compass bracket assembly, the generator drive and standby power module, and the air conditioning module, as applicable. The existing AD also currently requires, among other actions, inspecting for wire length and for damage of the connectors and the wire bundles, and doing applicable corrective actions if necessary. This new AD requires an additional operational test of the P5–14 panel. This AD results from a report of an electrical burning smell in the flight compartment. We are issuing this AD to prevent wire bundles from contacting the overhead dripshield panel and modules in the P5 overhead panel, which could result in electrical arcing and shorting of the electrical connector and consequent loss of several critical systems essential for safe flight; and to ensure proper operation of the passenger oxygen system. If an improperly functioning passenger PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 41607 oxygen system goes undetected, the passenger oxygen mask could fail to deploy and result in possible incapacitation of passengers during a depressurization event. DATES: This AD becomes effective September 22, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 22, 2009. On June 22, 2006 (71 FR 28766, May 18, 2006), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Binh Tran, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6485; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006–10–17, amendment 39–14601 (71 FR 28766, May 18, 2006). The existing AD applies to certain Boeing Model 737–600, –700, –700C, –800, and –900 series airplanes. That NPRM was published in the Federal Register on October 31, 2008 (73 FR 64894). That NPRM proposed to continue to require replacing brackets that hold the P5 panel to the airplane structure, the standby compass bracket assembly, the generator drive and E:\FR\FM\18AUR1.SGM 18AUR1 41608 Federal Register / Vol. 74, No. 158 / Tuesday, August 18, 2009 / Rules and Regulations standby power module, and the air conditioning module. That NPRM also proposed to continue to require, among other actions, inspecting for wire length and for damage of the connectors and the wire bundles and doing applicable corrective actions if necessary. That NPRM also proposed to require an additional operational test of the P5–14 panel. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Align AD Action With Related Service Bulletin One commenter, Boeing, requests that the NPRM wording for paragraph (f)(4) be revised to align with Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008. Boeing states that the current wording in the NPRM indicates that the standby compass bracket assembly must be replaced with a new assembly. Boeing states that Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, states that the standby compass bracket assembly need not be replaced for all groups of airplanes. Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, also states to replace the standby compass bracket if necessary. We agree that clarification may be necessary. Paragraph (f)(4) is a restatement of actions required by AD 2006–10–17, and is retained in this supersedure. Paragraph (f) of this AD states that the corrective actions (including replacing the standby compass bracket assembly as required by paragraph (f)(4) of this AD) must be done, as applicable. In addition, we note that a new requirement of this AD, paragraph (i) of this AD, requires that after the effective date of this AD, only Revision 3 of Boeing Service Bulletin 737–24A1141, dated February 20, 2008, be used to do all applicable actions. We have not made any changes to the AD in this regard. cprice-sewell on DSKDVH8Z91PROD with RULES Request To Clarify Terminology One commenter, the Air Transport Association (ATA), on behalf of its member Delta Airlines, requests that the terminology in Boeing Service Bulletin 737–24A1141 be clarified. In its comment, Delta states that it believes that Boeing Service Bulletin 737– 24A1141 contains material that is vague in nature, which would leave information subject to interpretation. VerDate Nov<24>2008 14:34 Aug 17, 2009 Jkt 217001 Delta states that Boeing Service Bulletin 737–24A1141 includes figures that contain statements such as, ‘‘Some airplanes may have different wires, panels or connectors’’ (e.g., in Figures 6–11 and 94 of the service bulletin). Delta is concerned that statements such as these, when dealing with compliance situations in which many different individuals are left to determine the intent and method prescribed by such instructions, can lead to problems determining the state of compliance of aircraft that have had work accomplished per the required accomplishment instructions. In the past, this has led to the grounding of airplanes at significant expense to the airlines, while confusion over the interpretation of said instructions is determined and resolved. Therefore, Delta believes that either Boeing Service Bulletin 737–24A1141 should be revised to clarify the meaning of vague terms (e.g., ‘‘typical’’), or the AD should include notes to accomplish the same intent. Delta states that failure to clarify the vague terms will likely lead to the same compliance issues that operators previously experienced with the B737 Rudder System Enhancement Program (AD 2007–03–07, Amendment 39– 14918, 72 FR 4625, February 1, 2007) and MD88 auxiliary hydraulic pump feeder wire inspection/modification (AD 2006–15–15, Amendment 39–14696, 71 FR 43035, July 31, 2006). We find that clarification of certain material contained in Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, is necessary. We discussed the material referenced by the commenter as ‘‘vague’’ with Boeing to clarify the intended meaning. Boeing noted that Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, was initially released in January 2004, and since then has been revised three times (December 2004, December 2005, and February 2008) to update and correct information. As specified in Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, required actions include: replacing brackets to lower the P5 overhead panel to increase the space between the wire bundles and the dripshield panel and modules; inspecting to determine if unwanted wire length or damage exists; retying the wire bundle or reterminating the wire bundle into the connector to eliminate the unwanted wire; and repairing damaged wire and using teflon tape, nylon sheet, and lacing tape to give greater protection to the wire bundles. Also, depending on airplane configuration, the service bulletin PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 specifies replacing the standby compass bracket assembly with a new assembly, and replacing the stud assemblies with new assemblies. Boeing clarified that the P5 overhead panel varies from customer to customer, as indicated in the 98 figures contained in Boeing Service Bulletin 737– 24A1141, Revision 3, dated February 20, 2008. Boeing explains that the phrase questioned by the commenter—i.e., ‘‘Some airplanes may have different wires, panels or connectors’’—was used in the illustrations in the figures to indicate that the configuration on any given customer’s airplane may be different from that shown in the illustrations. The illustrations simply provide examples of various configurations an operator might find; therefore, the information provided in the illustrations of the figures is for reference. Boeing explained further that the word ‘‘typical’’ is intended to represent a configuration that is in more than one location within an illustration. Additionally, while accomplishment of the steps specified in the tables of the figures is required, the illustrations are simply examples of the wiring configuration. In addition, we find that the word ‘‘unwanted’’ requires clarification. That term is used in various locations in the service bulletin in conjunction with wire length conditions—e.g., paragraph 3.B.9. of the Accomplishment Instructions states to ‘‘Inspect the connectors and the wire bundles in the rear, P5 aft panel to determine if unwanted wire length exists in Group 1–22 airplanes. See Figure 6.’’ We clarify that the General Information section of the Accomplishment Instructions of Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, references Boeing Standard Wiring Practices Manual (SWPM) 20–10–11 for wire installation procedures, including defining the amount of slack and making sure that all wire slack is securely tied into the parent harness or clamped. Additionally, it should be noted that tables found in certain figures of Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008 (Figure 6, for example), refer operators to the SWPM for general conditions for wire installation. We have revised this final rule to include new Note 2 and Note 3 to clarify the meaning of the terminology discussed previously. E:\FR\FM\18AUR1.SGM 18AUR1 Federal Register / Vol. 74, No. 158 / Tuesday, August 18, 2009 / Rules and Regulations Updated Contact Information for Alternative Methods of Compliance (AMOCs) We have updated the contact information for paragraph (k) of this final rule. actions required by this AD for U.S. operators is $1,680 or $1,840 per airplane, depending on the airplane configuration. Authority for This Rulemaking Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the change described previously. We also determined that this change will not increase the economic burden on any operator or increase the scope of the AD. cprice-sewell on DSKDVH8Z91PROD with RULES Costs of Compliance There are about 740 airplanes of the affected design in the worldwide fleet. This AD affects about 333 airplanes of U.S. registry. For all airplanes, the required inspection, replacements, and wiring change that are required by AD 2006– 10–17 and retained in this AD take about 16 or 18 work hours per airplane (depending on airplane configuration), at an average labor rate of $80 per work hour. Required parts cost about $10,231 or $11,139 per airplane (depending on the kit). Based on these figures, the estimated cost of the replacements and inspections required by this AD for U.S. operators is between $3,833,163 and $4,188,807, or between $11,511 and $12,579 per airplane. For certain airplanes, the modification of the generator drive and standby power module assembly that is required by AD 2006–10–17 and retained in this AD takes about 2 work hours per airplane, at an average labor rate of $80 per work hour. The airplane manufacturer states that it will supply required parts to operators at no cost. Based on these figures, the estimated cost of this modification required by this AD is $160 per airplane. For certain other airplanes, the modification of the air conditioning module assembly that is required by AD 2006–10–17 and retained in this AD takes about 1 work hour per airplane, at an average labor rate of $80 per work hour. The airplane manufacturer states that it will supply required parts to operators at no cost. Based on these figures, the estimated cost of this modification required by this AD is $80 per airplane. For certain airplanes, the new action takes about 21 or 23 work hours per airplane depending on the airplane configuration, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the new VerDate Nov<24>2008 14:34 Aug 17, 2009 Jkt 217001 Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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 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, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 41609 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 39–14601 (71 FR 28766, May 18, 2006) and by adding the following new airworthiness directive (AD): ■ 2009–16–07 Boeing: Amendment 39–15990. Docket No. FAA–2008–1143; Directorate Identifier 2008–NM–136–AD. Effective Date (a) This AD becomes effective September 22, 2009. Affected ADs (b) This AD supersedes AD 2006–10–17. Applicability (c) This AD applies to Boeing Model 737– 600, –700, –700C, –800, and –900 series airplanes, certificated in any category; as identified in Boeing Service Bulletin 737– 24A1141, Revision 3, dated February 20, 2008. Unsafe Condition (d) This AD results from a report of an electrical burning smell in the flight compartment. We are issuing this AD to prevent wire bundles from contacting the overhead dripshield panel and modules in the P5 overhead panel, which could result in electrical arcing and shorting of the electrical connector and consequent loss of several critical systems essential for safe flight; and to ensure proper operation of the passenger oxygen system. If an improperly functioning passenger oxygen system goes undetected, the passenger oxygen mask could fail to deploy and result in possible incapacitation of passengers during a depressurization event. 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 2006–10–17 Inspection/Replacements/Wiring Changes/ Corrective Actions (f) Within 36 months after June 22, 2006 (the effective date of AD 2006–10–17), do the applicable actions in paragraphs (f)(1) through (f)(5) of this AD by accomplishing all the applicable actions specified in the Accomplishment Instructions of Boeing Service Bulletin 737–24A1141, Revision 2, dated December 1, 2005, except as provided by paragraph (i) of this AD. Any applicable corrective actions must be done before further flight. (1) Replace the five brackets that hold the P5 panel to the airplane structure with new brackets; E:\FR\FM\18AUR1.SGM 18AUR1 41610 Federal Register / Vol. 74, No. 158 / Tuesday, August 18, 2009 / Rules and Regulations (2) Do a general visual inspection for wire length and damage of the connectors and the wire bundles, and applicable corrective actions; (3) Make wiring changes; (4) Replace the standby compass bracket assembly with a new assembly; and (5) Replace the stud assemblies with new assemblies. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (g) Actions done before June 22, 2006, in accordance with Boeing Alert Service Bulletin 737–24A1141, Revision 1, dated December 23, 2004, are acceptable for compliance with the requirements of paragraph (f) of this AD. Concurrent Requirements (h) Before or concurrently with the requirements of paragraph (f) of this AD, do the applicable action specified in Table 1 of this AD. TABLE 1—CONCURRENT REQUIREMENTS For airplanes identified in Boeing component Service Bulletin— Action (1) 233A3205–24–01, dated July 26, 2001 ........ Modify the generator drive and standby power module assembly in accordance with the Accomplishment Instructions of Boeing Component Service Bulletin 233A3205–24–01, dated July 26, 2001. Modify the air conditioning module assembly in accordance with the Accomplishment Instructions of Boeing Component Service Bulletin 69-37319–21–02, Revision 1, dated August 30, 2001. (2) 69–37319–21–02, Revision 1, dated August 30, 2001. New Actions Required by This AD New Service Bulletin Revision (i) As of the effective date of this AD, use only the Accomplishment Instructions of Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, to do all the applicable actions required by paragraph (f) of this AD. Note 2: Accomplishment of the steps specified in the tables of the figures of Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008, is required. Due to the variability of airplane configurations, the illustrations in the figures are provided as examples. Note 3: Boeing Service Bulletin 737– 24A1141, Revision 3, dated February 20, 2008, refers to ‘‘unwanted’’ wire length. ‘‘Unwanted’’ wire length is any wire length that does not meet the wire length requirements specified in the Standard Wiring Practices Manual (SWPM). Additional Operational Test (j) For airplanes on which the actions required by paragraph (f) of this AD have been done in accordance with Boeing Service Bulletin 737–24A1141, Revision 2, dated December 1, 2005, before the effective date of this AD: Within 12 months after the effective date of this AD, do an operational test of the P5–14 panel in accordance with paragraphs 3.B.92. and 3.B.93., as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 737–24A1141, Revision 3, dated February 20, 2008. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Binh Tran, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6485; fax (425) 917–6590. Or, email information to 9–ANM–Seattle-ACO– AMOC–Requests@faa.gov. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) AMOCs approved previously in accordance with AD 2006–10–17 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (l) You must use the service information contained in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE Document Revision level Boeing Component Service Bulletin 233A3205–24–01 ....................................... Boeing Component Service Bulletin 69–37319–21–02 ....................................... Boeing Service Bulletin 737–24A1141 ................................................................. Original .................................................. 1 ............................................................ 3 ............................................................ cprice-sewell on DSKDVH8Z91PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 3 Date July 26, 2001. August 30, 2001. February 20, 2008. of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE Document Revision level Boeing Service Bulletin 737–24A1141 ................................................................. 3 ............................................................ VerDate Nov<24>2008 14:34 Aug 17, 2009 Jkt 217001 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 E:\FR\FM\18AUR1.SGM 18AUR1 Date February 20, 2008. 41611 Federal Register / Vol. 74, No. 158 / Tuesday, August 18, 2009 / Rules and Regulations (2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in Table 4 of this AD on June 22, 2006 (71 FR 28766, May 18, 2006). TABLE 4—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Document Revision level Boeing Component Service Bulletin 233A3205–24–01 ....................................... Boeing Component Service Bulletin 69–37319–21–02 ....................................... Original .................................................. 1 ............................................................ (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 7, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–19180 Filed 8–17–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0004; Directorate Identifier 2008–NM–160–AD; Amendment 39–15995; AD 2009–17–04] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. cprice-sewell on DSKDVH8Z91PROD with RULES AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation VerDate Nov<24>2008 14:34 Aug 17, 2009 Jkt 217001 product. The MCAI describes the unsafe condition as: One case of elevator servo-control disconnection has been experienced on an aircraft of the A320 family. Failure occurred at the servo-control rod eye-end. Further to this finding, additional inspections have revealed cracking at the same location on a number of other servo-control rod eye-ends. In one case, both actuators of the same elevator surface were affected. * * * A dual servo-control disconnection on the same elevator could result in an uncontrolled surface, the elevator surface being neither actuated nor damped, which could lead to reduced control of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective September 22, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 22, 2009. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on January 13, 2009 (74 FR 1646). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: One case of elevator servo-control disconnection has been experienced on an aircraft of the A320 family. Failure occurred at the servo-control rod eye-end. Further to PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 Date July 26, 2001. August 30, 2001. this finding, additional inspections have revealed cracking at the same location on a number of other servo-control rod eye-ends. In one case, both actuators of the same elevator surface were affected. The root cause of the cracking has not yet been determined and tests are ongoing. It is anticipated that further actions will be required. A dual servo-control disconnection on the same elevator could result in an uncontrolled surface, the elevator surface being neither actuated nor damped, which could lead to reduced control of the aircraft. For the reason described above, this AD requires a one-time inspection [for cracking] of the elevator servo-control rod eye-ends and, in case of findings, the accomplishment of corrective actions. The corrective actions include replacing any cracked rod eye-end with a serviceable unit and re-adjusting the elevator servo-control. You may obtain further information by examining the MCAI in the AD docket. Explanation of Revised Service Information Airbus has issued All Operators Telex (AOT) A320–27A1186, Revision 04, dated April 3, 2009. (We referred to Airbus AOT A320–27A1186, dated June 23, 2008, in the NPRM as the appropriate source of service information for doing the proposed actions.) Airbus has also issued AOT A320–27A1186, Revision 01, dated August 11, 2008; Revision 02, dated March 30, 2009; and Revision 03, dated April 1, 2009. Airbus issued Revision 01, Revision 03, and Revision 04 of the AOT to include minor improvements in the procedures. No additional work is necessary for airplanes on which Airbus AOT A320–27A1186, dated June 23, 2008; Revision 01, dated August 11, 2008; Revision 02, dated March 30, 2009; or Revision 03, dated April 1, 2009; has been accomplished before the effective date of this AD. We have revised paragraphs (f)(1) through (f)(5), and paragraph (h) of this AD, to include Airbus AOT A320–27A1186, Revision 04, dated April 3, 2009. We have also added a new paragraph (f)(6) to this AD to include credit for accomplishing the actions before the effective date of this AD using the previously issued AOTs. Airbus AOT A320–27A1186, Revision 02, dated March 30, 2009, reduces the E:\FR\FM\18AUR1.SGM 18AUR1

Agencies

[Federal Register Volume 74, Number 158 (Tuesday, August 18, 2009)]
[Rules and Regulations]
[Pages 41607-41611]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-19180]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1143; Directorate Identifier 2008-NM-136-AD;
Amendment 39-15990; AD 2009-16-07]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes. That AD currently requires replacing
brackets that hold the P5 panel to the airplane structure, the standby
compass bracket assembly, the generator drive and standby power module,
and the air conditioning module, as applicable. The existing AD also
currently requires, among other actions, inspecting for wire length and
for damage of the connectors and the wire bundles, and doing applicable
corrective actions if necessary. This new AD requires an additional
operational test of the P5-14 panel. This AD results from a report of
an electrical burning smell in the flight compartment. We are issuing
this AD to prevent wire bundles from contacting the overhead dripshield
panel and modules in the P5 overhead panel, which could result in
electrical arcing and shorting of the electrical connector and
consequent loss of several critical systems essential for safe flight;
and to ensure proper operation of the passenger oxygen system. If an
improperly functioning passenger oxygen system goes undetected, the
passenger oxygen mask could fail to deploy and result in possible
incapacitation of passengers during a depressurization event.

DATES: This AD becomes effective September 22, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of September 22,
2009.
On June 22, 2006 (71 FR 28766, May 18, 2006), the Director of the
Federal Register approved the incorporation by reference of certain
other publications listed in the AD.

ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Binh Tran, Systems and Equipment
Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6485;
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2006-10-17, amendment
39-14601 (71 FR 28766, May 18, 2006). The existing AD applies to
certain Boeing Model 737-600, -700, -700C, -800, and -900 series
airplanes. That NPRM was published in the Federal Register on October
31, 2008 (73 FR 64894). That NPRM proposed to continue to require
replacing brackets that hold the P5 panel to the airplane structure,
the standby compass bracket assembly, the generator drive and

[[Page 41608]]

standby power module, and the air conditioning module. That NPRM also
proposed to continue to require, among other actions, inspecting for
wire length and for damage of the connectors and the wire bundles and
doing applicable corrective actions if necessary. That NPRM also
proposed to require an additional operational test of the P5-14 panel.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.

Request To Align AD Action With Related Service Bulletin

One commenter, Boeing, requests that the NPRM wording for paragraph
(f)(4) be revised to align with Boeing Service Bulletin 737-24A1141,
Revision 3, dated February 20, 2008. Boeing states that the current
wording in the NPRM indicates that the standby compass bracket assembly
must be replaced with a new assembly. Boeing states that Boeing Service
Bulletin 737-24A1141, Revision 3, dated February 20, 2008, states that
the standby compass bracket assembly need not be replaced for all
groups of airplanes. Boeing Service Bulletin 737-24A1141, Revision 3,
dated February 20, 2008, also states to replace the standby compass
bracket if necessary.
We agree that clarification may be necessary. Paragraph (f)(4) is a
restatement of actions required by AD 2006-10-17, and is retained in
this supersedure. Paragraph (f) of this AD states that the corrective
actions (including replacing the standby compass bracket assembly as
required by paragraph (f)(4) of this AD) must be done, as applicable.
In addition, we note that a new requirement of this AD, paragraph (i)
of this AD, requires that after the effective date of this AD, only
Revision 3 of Boeing Service Bulletin 737-24A1141, dated February 20,
2008, be used to do all applicable actions. We have not made any
changes to the AD in this regard.

Request To Clarify Terminology

One commenter, the Air Transport Association (ATA), on behalf of
its member Delta Airlines, requests that the terminology in Boeing
Service Bulletin 737-24A1141 be clarified. In its comment, Delta states
that it believes that Boeing Service Bulletin 737-24A1141 contains
material that is vague in nature, which would leave information subject
to interpretation.
Delta states that Boeing Service Bulletin 737-24A1141 includes
figures that contain statements such as, ``Some airplanes may have
different wires, panels or connectors'' (e.g., in Figures 6-11 and 94
of the service bulletin). Delta is concerned that statements such as
these, when dealing with compliance situations in which many different
individuals are left to determine the intent and method prescribed by
such instructions, can lead to problems determining the state of
compliance of aircraft that have had work accomplished per the required
accomplishment instructions. In the past, this has led to the grounding
of airplanes at significant expense to the airlines, while confusion
over the interpretation of said instructions is determined and
resolved. Therefore, Delta believes that either Boeing Service Bulletin
737-24A1141 should be revised to clarify the meaning of vague terms
(e.g., ``typical''), or the AD should include notes to accomplish the
same intent.
Delta states that failure to clarify the vague terms will likely
lead to the same compliance issues that operators previously
experienced with the B737 Rudder System Enhancement Program (AD 2007-
03-07, Amendment 39-14918, 72 FR 4625, February 1, 2007) and MD88
auxiliary hydraulic pump feeder wire inspection/modification (AD 2006-
15-15, Amendment 39-14696, 71 FR 43035, July 31, 2006).
We find that clarification of certain material contained in Boeing
Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, is
necessary. We discussed the material referenced by the commenter as
``vague'' with Boeing to clarify the intended meaning.
Boeing noted that Boeing Service Bulletin 737-24A1141, Revision 3,
dated February 20, 2008, was initially released in January 2004, and
since then has been revised three times (December 2004, December 2005,
and February 2008) to update and correct information. As specified in
Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20,
2008, required actions include: replacing brackets to lower the P5
overhead panel to increase the space between the wire bundles and the
dripshield panel and modules; inspecting to determine if unwanted wire
length or damage exists; retying the wire bundle or reterminating the
wire bundle into the connector to eliminate the unwanted wire; and
repairing damaged wire and using teflon tape, nylon sheet, and lacing
tape to give greater protection to the wire bundles. Also, depending on
airplane configuration, the service bulletin specifies replacing the
standby compass bracket assembly with a new assembly, and replacing the
stud assemblies with new assemblies.
Boeing clarified that the P5 overhead panel varies from customer to
customer, as indicated in the 98 figures contained in Boeing Service
Bulletin 737-24A1141, Revision 3, dated February 20, 2008. Boeing
explains that the phrase questioned by the commenter--i.e., ``Some
airplanes may have different wires, panels or connectors''--was used in
the illustrations in the figures to indicate that the configuration on
any given customer's airplane may be different from that shown in the
illustrations. The illustrations simply provide examples of various
configurations an operator might find; therefore, the information
provided in the illustrations of the figures is for reference. Boeing
explained further that the word ``typical'' is intended to represent a
configuration that is in more than one location within an illustration.
Additionally, while accomplishment of the steps specified in the tables
of the figures is required, the illustrations are simply examples of
the wiring configuration.
In addition, we find that the word ``unwanted'' requires
clarification. That term is used in various locations in the service
bulletin in conjunction with wire length conditions--e.g., paragraph
3.B.9. of the Accomplishment Instructions states to ``Inspect the
connectors and the wire bundles in the rear, P5 aft panel to determine
if unwanted wire length exists in Group 1-22 airplanes. See Figure 6.''
We clarify that the General Information section of the Accomplishment
Instructions of Boeing Service Bulletin 737-24A1141, Revision 3, dated
February 20, 2008, references Boeing Standard Wiring Practices Manual
(SWPM) 20-10-11 for wire installation procedures, including defining
the amount of slack and making sure that all wire slack is securely
tied into the parent harness or clamped. Additionally, it should be
noted that tables found in certain figures of Boeing Service Bulletin
737-24A1141, Revision 3, dated February 20, 2008 (Figure 6, for
example), refer operators to the SWPM for general conditions for wire
installation.
We have revised this final rule to include new Note 2 and Note 3 to
clarify the meaning of the terminology discussed previously.

[[Page 41609]]

Updated Contact Information for Alternative Methods of Compliance
(AMOCs)

We have updated the contact information for paragraph (k) of this
final rule.

Conclusion

We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the change described previously. We also determined that
this change will not increase the economic burden on any operator or
increase the scope of the AD.

Costs of Compliance

There are about 740 airplanes of the affected design in the
worldwide fleet. This AD affects about 333 airplanes of U.S. registry.
For all airplanes, the required inspection, replacements, and
wiring change that are required by AD 2006-10-17 and retained in this
AD take about 16 or 18 work hours per airplane (depending on airplane
configuration), at an average labor rate of $80 per work hour. Required
parts cost about $10,231 or $11,139 per airplane (depending on the
kit). Based on these figures, the estimated cost of the replacements
and inspections required by this AD for U.S. operators is between
$3,833,163 and $4,188,807, or between $11,511 and $12,579 per airplane.
For certain airplanes, the modification of the generator drive and
standby power module assembly that is required by AD 2006-10-17 and
retained in this AD takes about 2 work hours per airplane, at an
average labor rate of $80 per work hour. The airplane manufacturer
states that it will supply required parts to operators at no cost.
Based on these figures, the estimated cost of this modification
required by this AD is $160 per airplane.
For certain other airplanes, the modification of the air
conditioning module assembly that is required by AD 2006-10-17 and
retained in this AD takes about 1 work hour per airplane, at an average
labor rate of $80 per work hour. The airplane manufacturer states that
it will supply required parts to operators at no cost. Based on these
figures, the estimated cost of this modification required by this AD is
$80 per airplane.
For certain airplanes, the new action takes about 21 or 23 work
hours per airplane depending on the airplane configuration, at an
average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the new actions required by this AD for U.S.
operators is $1,680 or $1,840 per airplane, depending on the airplane
configuration.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14601 (71 FR 28766, May 18, 2006) and by adding
the following new airworthiness directive (AD):

2009-16-07 Boeing: Amendment 39-15990. Docket No. FAA-2008-1143;
Directorate Identifier 2008-NM-136-AD.

Effective Date

(a) This AD becomes effective September 22, 2009.

Affected ADs

(b) This AD supersedes AD 2006-10-17.

Applicability

(c) This AD applies to Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes, certificated in any category; as
identified in Boeing Service Bulletin 737-24A1141, Revision 3, dated
February 20, 2008.

Unsafe Condition

(d) This AD results from a report of an electrical burning smell
in the flight compartment. We are issuing this AD to prevent wire
bundles from contacting the overhead dripshield panel and modules in
the P5 overhead panel, which could result in electrical arcing and
shorting of the electrical connector and consequent loss of several
critical systems essential for safe flight; and to ensure proper
operation of the passenger oxygen system. If an improperly
functioning passenger oxygen system goes undetected, the passenger
oxygen mask could fail to deploy and result in possible
incapacitation of passengers during a depressurization event.

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 2006-10-17

Inspection/Replacements/Wiring Changes/Corrective Actions

(f) Within 36 months after June 22, 2006 (the effective date of
AD 2006-10-17), do the applicable actions in paragraphs (f)(1)
through (f)(5) of this AD by accomplishing all the applicable
actions specified in the Accomplishment Instructions of Boeing
Service Bulletin 737-24A1141, Revision 2, dated December 1, 2005,
except as provided by paragraph (i) of this AD. Any applicable
corrective actions must be done before further flight.
(1) Replace the five brackets that hold the P5 panel to the
airplane structure with new brackets;

[[Page 41610]]

(2) Do a general visual inspection for wire length and damage of
the connectors and the wire bundles, and applicable corrective
actions;
(3) Make wiring changes;
(4) Replace the standby compass bracket assembly with a new
assembly; and
(5) Replace the stud assemblies with new assemblies.

Note 1: For the purposes of this AD, a general visual
inspection is: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to ensure visual access to all surfaces in the inspection
area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight,
or droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''

(g) Actions done before June 22, 2006, in accordance with Boeing
Alert Service Bulletin 737-24A1141, Revision 1, dated December 23,
2004, are acceptable for compliance with the requirements of
paragraph (f) of this AD.

Concurrent Requirements

(h) Before or concurrently with the requirements of paragraph
(f) of this AD, do the applicable action specified in Table 1 of
this AD.

Table 1--Concurrent Requirements
------------------------------------------------------------------------
For airplanes identified in
Boeing component Service Action
Bulletin--
------------------------------------------------------------------------
(1) 233A3205-24-01, dated Modify the generator drive and standby
July 26, 2001. power module assembly in accordance with
the Accomplishment Instructions of
Boeing Component Service Bulletin
233A3205-24-01, dated July 26, 2001.
(2) 69-37319-21-02, Revision Modify the air conditioning module
1, dated August 30, 2001. assembly in accordance with the
Accomplishment Instructions of Boeing
Component Service Bulletin 69[dash]37319-
21-02, Revision 1, dated August 30,
2001.
------------------------------------------------------------------------

New Actions Required by This AD

New Service Bulletin Revision

(i) As of the effective date of this AD, use only the
Accomplishment Instructions of Boeing Service Bulletin 737-24A1141,
Revision 3, dated February 20, 2008, to do all the applicable
actions required by paragraph (f) of this AD.

Note 2: Accomplishment of the steps specified in the tables of
the figures of Boeing Service Bulletin 737-24A1141, Revision 3,
dated February 20, 2008, is required. Due to the variability of
airplane configurations, the illustrations in the figures are
provided as examples.

Note 3: Boeing Service Bulletin 737-24A1141, Revision 3, dated
February 20, 2008, refers to ``unwanted'' wire length. ``Unwanted''
wire length is any wire length that does not meet the wire length
requirements specified in the Standard Wiring Practices Manual
(SWPM).

Additional Operational Test

(j) For airplanes on which the actions required by paragraph (f)
of this AD have been done in accordance with Boeing Service Bulletin
737-24A1141, Revision 2, dated December 1, 2005, before the
effective date of this AD: Within 12 months after the effective date
of this AD, do an operational test of the P5-14 panel in accordance
with paragraphs 3.B.92. and 3.B.93., as applicable, of the
Accomplishment Instructions of Boeing Service Bulletin 737-24A1141,
Revision 3, dated February 20, 2008.

Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, Seattle Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to Attn: Binh
Tran, Aerospace Engineer, Systems and Equipment Branch, ANM-130S,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6485; fax (425)
917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(3) AMOCs approved previously in accordance with AD 2006-10-17
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

(l) You must use the service information contained in Table 2 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.

Table 2--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing Component Service Bulletin Original.................... July 26, 2001.
233A3205-24-01.
Boeing Component Service Bulletin 69- 1........................... August 30, 2001.
37319-21-02.
Boeing Service Bulletin 737-24A1141...... 3........................... February 20, 2008.
----------------------------------------------------------------------------------------------------------------

(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

Table 3--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 737-24A1141...... 3........................... February 20, 2008.
----------------------------------------------------------------------------------------------------------------

[[Page 41611]]

(2) The Director of the Federal Register previously approved
the incorporation by reference of the service information contained
in Table 4 of this AD on June 22, 2006 (71 FR 28766, May 18, 2006).

Table 4--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing Component Service Bulletin Original.................... July 26, 2001.
233A3205-24-01.
Boeing Component Service Bulletin 69- 1........................... August 30, 2001.
37319-21-02.
----------------------------------------------------------------------------------------------------------------

(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(5) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Issued in Renton, Washington, on August 7, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-19180 Filed 8-17-09; 8:45 am]
BILLING CODE 4910-13-P

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