Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes, 68512-68515 [E9-29964]

Download as PDF 68512 Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations 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 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] Unsafe Condition (d) This AD results from Turbomeca identifying five additional reduction gearboxes (module M05) affected, and adding an alternative optional terminating action to the repetitive visual inspections. We are issuing this AD to prevent uncommanded inflight engine shutdown, possible engine fire, and an emergency autorotation landing. 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. Initial Visual Inspection Before Further Flight (f) Before further flight: (1) Visually inspect the reduction gearbox (module M05) lubrication duct for oil leakage. Use paragraph 1.C.(1)(a), paragraph 2.A., and Figure 2 of Turbomeca S.A. MSB No. A292 72 0825, Version B, dated October 6, 2009, to do the inspection. (2) If oil leakage is found: (i) Repair the reduction gearbox (module M05) lubrication duct by filling it with black CAF 33 elastomer. Use paragraphs 2.B.1 through 2.B.1.(a)3 3.2, Figure 3, and Figure 4 in Turbomeca S.A. MSB No. A292 72 0825, Version B, dated October 6, 2009, to do the repair; or (ii) Repair the reduction gearbox (module M05) lubrication duct by installing a steel plug. Use paragraphs 2.B.1(b)1 through 2.B.1(b)7, and Figure 5 in Turbomeca S.A. MSB No. A292 72 0825, Version B, dated October 6, 2009, to do the repair. AD if requested using the procedures found in 14 CFR 39.19. Related Information (k) European Aviation Safety Agency emergency airworthiness directive 2009– 0245–E, dated November 10, 2009, also addresses the subject of this AD. Contact Information (l) For further information, contact: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (m) You must use Turbomeca Mandatory Service Bulletin No. A292 72 0825, Version B, dated October 6, 2009, to identify the serial numbers of reduction gearboxes (module M05) affected by this AD, and to perform the inspections and repairs required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00, fax (33) 05 59 74 45 15. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or 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/ cfr/ibr-locations.html. Special Flight Permits (n) Under 14 CFR part 39.23, special flight permits for this AD are prohibited. Issued in Burlington, Massachusetts, on December 10, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–29985 Filed 12–24–09; 8:45 am] Repetitive Visual Inspections (g) If no oil leakage is found, repeat the visual inspection every four flight hours, or after the last flight of each day, whichever comes first. (h) The actions required by paragraph (g) of this AD may be performed by the owner/ operator holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 and 14 CFR 91.417(a)(2)(v). BILLING CODE 4910–13–P RIN 2120–AA64 Affected ADs (b) This AD supersedes AD 2009–12–51, Amendment 39–15952. Optional Terminating Action (i) As optional terminating action to the repetitive visual inspections in paragraph (g) of this AD, repair the affected reduction gearbox (module M05) as specified in paragraph (f)(2) of this AD. Applicability (c) This AD applies to Turbomeca Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines if Alternative Methods of Compliance (j) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this 2. The FAA amends § 39.13 by removing Amendment 39–15952 (74 FR 31167, June 30, 2009), and by adding a new airworthiness directive, Amendment 39–16142, to read as follows: ■ 2009–26–07 Turbomeca: Amendment 39– 16142. Docket No. FAA–2009–0544; Directorate Identifier 2009–NE–17–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 12, 2010. erowe on DSK5CLS3C1PROD with RULES modified by Turbomeca Modification TU332 and fitted with a reduction gearbox (module M05) as listed by serial number in Figure 1 of Turbomeca Mandatory Service Bulletin (MSB) No. A292 72 0825, Version B, dated October 6, 2009. These engines are installed on, but not limited to, Eurocopter France AS350B, AS350BA, AS365N, AS350B1, AS350B2, Eurocopter Deutschland GmbH MBB–BK117–C1, Agusta A109K2, and Sikorsky S–76A+, S–76A++ and S–76C helicopters. VerDate Nov<24>2008 10:44 Dec 24, 2009 Jkt 220001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29087; Directorate Identifier 2007–NM–094–AD; Amendment 39–16139; AD 2009–26–04] 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. E:\FR\FM\28DER1.SGM 28DER1 Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737–600, –700, –700C, –800, and –900 series airplanes. This AD requires repetitive lubrication of the left and right main landing gear (MLG) forward trunnion pins; and an inspection for discrepancies of the transition radius, lead-in chamfer, and cross-bolt bore of the MLG forward trunnion pins, and repair or replacement if necessary. Doing the applicable inspections and repairs/ replacements, or overhauling the trunnion pins ends the repetitive lubrication requirements of this AD. For airplanes on which a certain repair is done, this AD requires repetitive inspections for discrepancies of the transition radius. This AD results from a report that the protective finishes on the forward trunnion pins for the left and right MLG might have been damaged during final assembly. We are issuing this AD to prevent cracking of the forward trunnion pin, which could result in fracture of the pin and consequent collapse of the MLG. DATES: This AD becomes effective February 1, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 1, 2010. 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. 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: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: 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 Comments Discussion The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Boeing Model 737–600, –700, –700C, –800, and –900 series airplanes. That supplemental NPRM was published in the Federal Register on August 5, 2009 (74 FR 38988). That supplemental NPRM proposed to require repetitive lubrication of the left and right main landing gear (MLG) forward trunnion pins; and an inspection for discrepancies of the transition radius, lead-in chamfer, and cross-bolt bore of the MLG forward trunnion pins, and repair or replacement if necessary. Doing the applicable inspections and repairs/replacements, or overhauling the trunnion pins, ends the repetitive lubrication requirements of the proposed AD. For airplanes on which a certain repair is done, the action proposed to require repetitive inspections for discrepancies of the transition radius. We provided the public the opportunity to participate in the development of this AD. We have considered the two comments received on the supplemental NPRM. Support for the Supplemental NPRM One commenter, Boeing, concurs with the content of the supplemental NPRM. 68513 Request for Added Language Korean Air (KA) requests that we add some of the referenced service bulletin language to further clarify the proposed AD. KA requests that we add the phrase ‘‘with MLG not removed (in situ)’’ to paragraph (h), and ‘‘transition radius, the lead-in chamfer and cross-bolt bore with MLG removed’’ to paragraph (i), of the supplemental NPRM. We partially agree. Adding language from Boeing Service Bulletin 737–32– 1376, Revision 2, dated August 6, 2008, can further clarify the actions in the AD. We have revised paragraph (h) of the AD to add ‘‘with MLG not removed (in situ)’’ as the commenter requests. We have also revised paragraph (i) of the AD to add ‘‘with the MLG removed;’’ however, reference to ‘‘the lead-in chamfer and cross-bolt bore’’ was already stated in paragraph (i) of the supplemental NPRM. We do not agree, however, to add a reference to ‘‘transition radius’’ to paragraph (i) of the AD. Although paragraph (i) of the AD does not specify to inspect the transition radius of the trunnion pin with the pin removed, that inspection, along with other tasks, would be covered by the typical maintenance requirements for overhauling the MLG. We have not changed the AD in this regard. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 890 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate is $80 per work hour. ESTIMATED COSTS erowe on DSK5CLS3C1PROD with RULES Action Work hours Repetitive lubrication ..................... Inspections (in situ) ....................... Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Nov<24>2008 10:44 Dec 24, 2009 Jkt 220001 Number of U.S.-registered airplanes Cost per airplane 2 2 $160 per lubrication cycle ............. $160 .............................................. rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 300 300 Fleet cost $48,000 per lubrication cycle. $48,000. detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, E:\FR\FM\28DER1.SGM 28DER1 68514 Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations 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: ■ 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. erowe on DSK5CLS3C1PROD with RULES § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2009–26–04 Boeing: Amendment 39–16139. Docket No. FAA–2007–29087; Directorate Identifier 2007–NM–094–AD. VerDate Nov<24>2008 10:44 Dec 24, 2009 Jkt 220001 Effective Date (a) This AD becomes effective February 1, 2010. Affected ADs (b) None. 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 737–32– 1376, Revision 2, dated August 6, 2008. Subject (d) Air Transport Association (ATA) of America Code 32: Landing Gear. Unsafe Condition (e) This AD results from a report that the protective finishes on the forward trunnion pins for the left and right main landing gear (MLG) might have been damaged during final assembly. We are issuing this AD to prevent cracking of the forward trunnion pin, which could result in fracture of the pin and consequent collapse of the MLG. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Lubrication or Overhaul (g) Within 30 days after the effective date of this AD: Lubricate the left and right MLG forward trunnion pins in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–32–1376, Revision 2, dated August 6, 2008. Repeat the lubrication at intervals not to exceed 30 days until all applicable requirements of paragraphs (h) and (i) of this AD have been accomplished. Overhauling the trunnion pin in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–32–1376, Revision 2, dated August 6, 2008, ends the repetitive lubrication requirements of this paragraph for that pin. Inspection and Corrective Actions (h) Within 60 months after the date of issuance of the original airworthiness certificate or date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later: Do a detailed inspection for discrepancies (corrosion, finish damage, surface deformation, or scratches) of the transition radius of the left and right MLG trunnion pins with MLG not removed (in situ); and if any discrepancy is found, repair or replace the trunnion pin before further flight. Do all actions in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737– 32–1376, Revision 2, dated August 6, 2008. If the repair specified in Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 737–32–1376, Revision 2, dated August 6, 2008, is done, within 24 months after doing the repair, do the detailed inspection of the transition radius, and do the inspection thereafter at intervals not to exceed 24 months until the trunnion pin is overhauled or replaced in accordance with PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 the Accomplishment Instructions of Boeing Service Bulletin 737–32–1376, Revision 2, dated August 6, 2008. (i) For airplanes on which the trunnion pin has not been replaced or overhauled: Within 120 months after the date of issuance of the original airworthiness certificate or date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later, do a detailed inspection for discrepancies of the lead-in chamfer and cross-bolt bore with the MLG removed; and if any discrepancy is found, repair or replace the trunnion pin before further flight. Do all actions in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–32–1376, Revision 2, dated August 6, 2008. No Report Required (j) Although Boeing Service Bulletin 737– 32–1376, Revision 2, dated August 6, 2008, specifies to send inspection reports to the manufacturer, this AD does not include that requirement. Credit for Actions Done Using Previous Issue of Service Information (k) Actions done before the effective date of this AD in accordance with Boeing Special Attention Service Bulletin 737–32–1376, dated May 12, 2005; or Boeing Service Bulletin 737–32–1376, Revision 1, dated March 19, 2007; are acceptable for compliance with the corresponding actions of this AD. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; 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) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. E:\FR\FM\28DER1.SGM 28DER1 Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations Material Incorporated by Reference (m) You must use Boeing Service Bulletin 737–32–1376, Revision 2, dated August 6, 2008, 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 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. (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 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 December 4, 2009. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–29964 Filed 12–24–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1195; Directorate Identifier 2009–NM–152–AD; Amendment 39–16145; AD 2008–11–01 R1] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 767–200, –300, –300F, and –400ER Series Airplanes erowe on DSK5CLS3C1PROD with RULES AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. Examining the AD Docket SUMMARY: The FAA is revising an existing airworthiness directive (AD), which applies to certain Model 767– 200, –300, –300F, and –400ER series airplanes. That AD currently requires revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 VerDate Nov<24>2008 10:44 Dec 24, 2009 Jkt 220001 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: This AD is effective January 12, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 12, 2010. On June 25, 2008 (73 FR 29414, May 21, 2008), the Director of the Federal Register approved the incorporation by reference of a certain other publication listed in the AD. We must receive any comments on this AD by February 26, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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. 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 street address for the Docket Office (telephone 800–647– PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 68515 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Douglas Bryant, Aerospace Engineer, Propulsion Branch, ANM–140S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6505; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion On May 8, 2008, we issued AD 2008– 11–01, Amendment 39–15523 (73 FR 29414, May 21, 2008). That AD applied to certain Model 767–200, –300, –300F, and –400ER series airplanes. That AD required revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also required an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. That AD resulted from a design review of the fuel tank systems. The actions specified in that AD are intended to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Critical design configuration control limitations (CDCCLs) are limitation requirements to preserve a critical ignition source prevention feature of the fuel tank system design that is necessary to prevent the occurrence of an unsafe condition. The purpose of a CDCCL is to provide instruction to retain the critical ignition source prevention feature during configuration change that may be caused by alterations, repairs, or maintenance actions. A CDCCL is not a periodic inspection. Actions Since AD Was Issued Since we issued that AD, we have determined that it is necessary to clarify the AD’s intended effect on spare and on-airplane fuel tank system components, regarding the use of maintenance manuals and instructions for continued airworthiness. Section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)) specifies the following: No person may operate an aircraft for which a manufacturer’s maintenance manual or instructions for continued airworthiness has been issued that contains an airworthiness limitation section unless the mandatory * * * procedures * * * have been complied with. E:\FR\FM\28DER1.SGM 28DER1

Agencies

[Federal Register Volume 74, Number 247 (Monday, December 28, 2009)]
[Rules and Regulations]
[Pages 68512-68515]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29964]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29087; Directorate Identifier 2007-NM-094-AD; 
Amendment 39-16139; AD 2009-26-04]
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.

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

[[Page 68513]]

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 737-600, -700, -700C, -800, and -900 series 
airplanes. This AD requires repetitive lubrication of the left and 
right main landing gear (MLG) forward trunnion pins; and an inspection 
for discrepancies of the transition radius, lead-in chamfer, and cross-
bolt bore of the MLG forward trunnion pins, and repair or replacement 
if necessary. Doing the applicable inspections and repairs/
replacements, or overhauling the trunnion pins ends the repetitive 
lubrication requirements of this AD. For airplanes on which a certain 
repair is done, this AD requires repetitive inspections for 
discrepancies of the transition radius. This AD results from a report 
that the protective finishes on the forward trunnion pins for the left 
and right MLG might have been damaged during final assembly. We are 
issuing this AD to prevent cracking of the forward trunnion pin, which 
could result in fracture of the pin and consequent collapse of the MLG.

DATES: This AD becomes effective February 1, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 1, 
2010.

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: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
917-6440; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that would apply to certain 
Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. 
That supplemental NPRM was published in the Federal Register on August 
5, 2009 (74 FR 38988). That supplemental NPRM proposed to require 
repetitive lubrication of the left and right main landing gear (MLG) 
forward trunnion pins; and an inspection for discrepancies of the 
transition radius, lead-in chamfer, and cross-bolt bore of the MLG 
forward trunnion pins, and repair or replacement if necessary. Doing 
the applicable inspections and repairs/replacements, or overhauling the 
trunnion pins, ends the repetitive lubrication requirements of the 
proposed AD. For airplanes on which a certain repair is done, the 
action proposed to require repetitive inspections for discrepancies of 
the transition radius.

Comments

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

Support for the Supplemental NPRM

    One commenter, Boeing, concurs with the content of the supplemental 
NPRM.

Request for Added Language

    Korean Air (KA) requests that we add some of the referenced service 
bulletin language to further clarify the proposed AD. KA requests that 
we add the phrase ``with MLG not removed (in situ)'' to paragraph (h), 
and ``transition radius, the lead-in chamfer and cross-bolt bore with 
MLG removed'' to paragraph (i), of the supplemental NPRM.
    We partially agree. Adding language from Boeing Service Bulletin 
737-32-1376, Revision 2, dated August 6, 2008, can further clarify the 
actions in the AD. We have revised paragraph (h) of the AD to add 
``with MLG not removed (in situ)'' as the commenter requests. We have 
also revised paragraph (i) of the AD to add ``with the MLG removed;'' 
however, reference to ``the lead-in chamfer and cross-bolt bore'' was 
already stated in paragraph (i) of the supplemental NPRM.
    We do not agree, however, to add a reference to ``transition 
radius'' to paragraph (i) of the AD. Although paragraph (i) of the AD 
does not specify to inspect the transition radius of the trunnion pin 
with the pin removed, that inspection, along with other tasks, would be 
covered by the typical maintenance requirements for overhauling the 
MLG. We have not changed the AD in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 890 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD. The average labor rate is $80 
per work hour.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                   Number of U.S.-
                Action                    Work hours        Cost per airplane        registered                          Fleet cost
                                                                                      airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive lubrication................               2  $160 per lubrication                  300  $48,000 per lubrication cycle.
                                                         cycle.
Inspections (in situ).................               2  $160.....................             300  $48,000.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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,

[[Page 68514]]

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 
adding the following new airworthiness directive (AD):

2009-26-04 Boeing: Amendment 39-16139. Docket No. FAA-2007-29087; 
Directorate Identifier 2007-NM-094-AD.

Effective Date

    (a) This AD becomes effective February 1, 2010.

Affected ADs

    (b) None.

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 737-32-1376, Revision 2, dated 
August 6, 2008.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Unsafe Condition

    (e) This AD results from a report that the protective finishes 
on the forward trunnion pins for the left and right main landing 
gear (MLG) might have been damaged during final assembly. We are 
issuing this AD to prevent cracking of the forward trunnion pin, 
which could result in fracture of the pin and consequent collapse of 
the MLG.

Compliance

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

Lubrication or Overhaul

    (g) Within 30 days after the effective date of this AD: 
Lubricate the left and right MLG forward trunnion pins in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 737-
32-1376, Revision 2, dated August 6, 2008. Repeat the lubrication at 
intervals not to exceed 30 days until all applicable requirements of 
paragraphs (h) and (i) of this AD have been accomplished. 
Overhauling the trunnion pin in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 737-32-1376, Revision 2, 
dated August 6, 2008, ends the repetitive lubrication requirements 
of this paragraph for that pin.

Inspection and Corrective Actions

    (h) Within 60 months after the date of issuance of the original 
airworthiness certificate or date of issuance of the original export 
certificate of airworthiness, or within 6 months after the effective 
date of this AD, whichever occurs later: Do a detailed inspection 
for discrepancies (corrosion, finish damage, surface deformation, or 
scratches) of the transition radius of the left and right MLG 
trunnion pins with MLG not removed (in situ); and if any discrepancy 
is found, repair or replace the trunnion pin before further flight. 
Do all actions in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 737-32-1376, Revision 2, dated August 6, 
2008. If the repair specified in Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 737-32-1376, Revision 2, 
dated August 6, 2008, is done, within 24 months after doing the 
repair, do the detailed inspection of the transition radius, and do 
the inspection thereafter at intervals not to exceed 24 months until 
the trunnion pin is overhauled or replaced in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 737-32-1376, 
Revision 2, dated August 6, 2008.
    (i) For airplanes on which the trunnion pin has not been 
replaced or overhauled: Within 120 months after the date of issuance 
of the original airworthiness certificate or date of issuance of the 
original export certificate of airworthiness, or within 6 months 
after the effective date of this AD, whichever occurs later, do a 
detailed inspection for discrepancies of the lead-in chamfer and 
cross-bolt bore with the MLG removed; and if any discrepancy is 
found, repair or replace the trunnion pin before further flight. Do 
all actions in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 737-32-1376, Revision 2, dated August 6, 
2008.

No Report Required

    (j) Although Boeing Service Bulletin 737-32-1376, Revision 2, 
dated August 6, 2008, specifies to send inspection reports to the 
manufacturer, this AD does not include that requirement.

Credit for Actions Done Using Previous Issue of Service Information

    (k) Actions done before the effective date of this AD in 
accordance with Boeing Special Attention Service Bulletin 737-32-
1376, dated May 12, 2005; or Boeing Service Bulletin 737-32-1376, 
Revision 1, dated March 19, 2007; are acceptable for compliance with 
the corresponding actions of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
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: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6440; 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) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

[[Page 68515]]

Material Incorporated by Reference

    (m) You must use Boeing Service Bulletin 737-32-1376, Revision 
2, dated August 6, 2008, 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 
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.
    (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 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 December 4, 2009.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-29964 Filed 12-24-09; 8:45 am]
BILLING CODE 4910-13-P
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