Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes, 61033-61036 [2011-24681]

Download as PDF 61033 Rules and Regulations Federal Register Vol. 76, No. 191 Monday, October 3, 2011 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1118; Directorate Identifier 2007–NM–318–AD; Amendment 39–16792; AD 2011–18–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for the products listed above. The existing AD currently requires reviewing the airplane maintenance records to determine whether an engine has been removed from the airplane since the airplane was manufactured. For airplanes on which an engine has been removed, the existing AD also requires an inspection of the aft engine mount to determine if the center link assembly is correctly installed, and follow-on actions if necessary. This new AD expands the applicability to include airplanes on which the engine has not been previously removed, and Model 737–900ER airplanes. This AD was prompted by reports indicating that operators found that the center link assembly for the aft engine mount was reversed on several airplanes that had not had an engine removed since delivery. We are issuing this AD to prevent increased structural loads on the aft engine mount, which could result in failure of the aft engine mount and consequent separation of the engine from the airplane. DATES: This AD is effective November 7, 2011. erowe on DSK2VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 14:42 Sep 30, 2011 Jkt 226001 The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 7, 2011. 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. You may review copies of the referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 (phone: 800–647–5527) is 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: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6450; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede airworthiness directive (AD) 2003–03– 01, Amendment 39–13025 (68 FR 4367, January 29, 2003). That AD applies to the specified products. The SNPRM published in the Federal Register on January 11, 2011 (76 FR 1552). The original NPRM (73 FR 64568, October 30, 2008) proposed to continue to require reviewing the airplane maintenance records to determine whether an engine has been removed PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 from the airplane since the airplane was manufactured. For airplanes on which an engine has been removed, the original NPRM also requires an inspection of the aft engine mount to determine if the center link assembly is correctly installed, and follow-on actions if necessary. The original NPRM also proposed to require those same actions on airplanes on which the engine has not previously been removed. The SNPRM proposed to further expand the applicability to include Model 737–900ER airplanes. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Supportive Comments Boeing and Continental Airlines concur with the SNPRM (76 FR 1552, January 11, 2011). Request for Information American Airlines stated that it has accomplished the actions required by AD 2003–03–01 (68 FR 4367, January 29, 2003) and the SNPRM (76 FR 1552, January 11, 2011), and although it will no longer be affected by the requirements in the SNPRM, asked the following questions: • What action has the original equipment manufacturer, Boeing, taken to prevent incorrect aft mount assembly installations? • Can Boeing specifically identify the procedures and/or best practices incorporated into their production process to prevent a recurrence of this type of event? We acknowledge the commenter’s concerns and provide the following responses: • Boeing Alert Service Bulletin 737– 71A1462, Revision 2, dated May 29, 2003; and Revision 3, dated May 20, 2004; specify marking of the hangar fitting (pylon structure) and center link (engine structure) assembly, which is the same as the marking incorporated previously in production. These marks ‘‘L,’’ ‘‘AFT,’’ and ‘‘R,’’ applied to both the hangar fitting and center link assembly will only be in close proximity if the center link is installed correctly. • Boeing has advised us that it has revised the instructions in its component maintenance manuals E:\FR\FM\03OCR1.SGM 03OCR1 61034 Federal Register / Vol. 76, No. 191 / Monday, October 3, 2011 / Rules and Regulations (assembly level) and aircraft maintenance manuals (installation level) to put special emphasis on the center link installation. Boeing also advised us that it implemented drawing changes affecting both production assembly and field installation of this part; these changes incorporated specific markings on both the center link assembly and the hanger fitting to which it is attached. Boeing noted that after 2003 the parts were marked with an ‘‘L’’ and ‘‘R’’ (left and right) to indicate the part orientation when assembled, and the hanger assembly was marked with ‘AFT’ at the center line. Boeing has also developed a shop aid for use at the facility where the parts are fabricated and assembled which helps the assembler confirm the correct orientation of the parts. We have made no change to the AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD affects 854 airplanes of U.S. registry. There are no new requirements in this AD; however, we have expanded the applicability of this AD. The current costs for this AD are recalculated for the convenience of affected operators, as follows: ESTIMATED COSTS Action Work hours Maintenance records review (required by AD 2003–03–01, Amendment 39– 13025 (68 FR 4367, January 29, 2003)) ..................................................... Inspection for correct installation of center link assembly (new required action) .............................................................................................................. 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. erowe on DSK2VPTVN1PROD with RULES 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), (3) Will not affect intrastate aviation in Alaska, and VerDate Mar<15>2010 14:42 Sep 30, 2011 Jkt 226001 Fleet cost 1 $0 $85 $72,590 1 0 85 72,590 (4) 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. –800, –900, and –900ER series airplanes, certificated in any category. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Unsafe Condition (e) This AD was prompted by reports indicating that operators found that the center link assembly for the aft engine mount was reversed on several airplanes that had not had an engine removed since delivery. We are issuing this AD to prevent increased structural loads on the aft engine mount, which could result in failure of the aft engine mount and consequent separation of the engine from the airplane. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2003–03–01, Amendment 39–13025 (68 FR 4367, January 29, 2003), and by adding the following new AD: ■ Regulatory Findings Cost per airplane Parts 2011–18–10 The Boeing Company: Amendment 39–16792; Docket No. FAA–2008–1118; Directorate Identifier 2007–NM–318–AD. Effective Date (a) This AD is effective November 7, 2011. Affected ADs (b) This AD supersedes AD 2003–03–01, Amendment 39–13025 (68 FR 4367, January 29, 2003). Applicability (c) This AD applies to all The Boeing Company Model 737–600, –700, –700C, PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Subject (d) Air Transport Association (ATA) of America Code 71: Powerplant. 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. Restatement of Requirements of AD 2003– 03–01 (68 FR 4367, January 29, 2003): Review of Maintenance Records (g) For Model 737–600, –700, –700C, –800, and –900 series airplanes: Within 90 days after February 13, 2003 (the effective date of AD 2003–03–01 (68 FR 4367, January 29, 2003)), review the airplane maintenance records to determine whether either engine has been removed since the airplane’s date of manufacture. If neither engine has been removed since the airplane’s date of manufacture, no further action is required by this paragraph. Inspection of Engines That Have Been Removed To Determine If Center Link Assembly Is Installed Correctly (h) For Model 737–600, –700, –700C, –800, and –900 series airplanes on which any installed engine has been removed from the airplane since the airplane’s date of manufacture: Within 90 days after February 13, 2003, do a one-time general visual inspection to determine if the center link E:\FR\FM\03OCR1.SGM 03OCR1 Federal Register / Vol. 76, No. 191 / Monday, October 3, 2011 / Rules and Regulations assembly of the aft engine mount is installed correctly, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–71A1462, Revision 1, dated November 7, 2002; or Revision 3, dated May 20, 2004. If the center link assembly is installed correctly, no further action is required by paragraph (h) or (i) of this AD for that engine. As of the effective date of this AD, use only Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004. 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, hanger 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.’’ Follow-On and Corrective Actions (i) For airplanes on which any center link assembly is found installed incorrectly during any inspection required by paragraph (h), (k), or (l) of this AD: Before further flight, do the actions specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–71A1462, Revision 1, dated November 7, 2002; or Revision 3, dated May 20, 2004; except that it is not necessary to submit a report of findings to the airplane manufacturer. As of the effective date of this AD, use only Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004. (1) Remove the center link assembly and install it correctly. (2) Perform a detailed inspection of the engine mounting lugs and engine turbine rear frame for cracking, yielding, buckling, or wear damage. (3) Perform a detailed inspection of the hardware for the aft engine mount; including the center link assembly, right link assembly, aft mount hanger assembly, and link pins; for cracking, yielding, buckling, or wear damage. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Repair (j) If any cracking, yielding, buckling, or wear damage is found during the inspections required by paragraphs (i)(2) and (i)(3) of this AD: Before further flight, replace the discrepant part with a new or serviceable part, or repair in accordance with a method approved in accordance with the procedures specified in paragraph (o) of this AD. 61035 New Requirements of This AD Inspection of Engines That Have Not Been Removed To Determine If Center Link Assembly Is Installed Correctly (k) For airplanes identified in Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004, on which any installed engine has not been removed from the airplane since the airplane’s date of manufacture: Within 90 days after the effective date of this AD, do a detailed inspection to determine if the center link assembly of the aft engine mount is installed correctly, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004. If the center link is installed correctly, no further action is required by this paragraph for that engine. Follow-On and Corrective Actions (l) For airplanes on which any center link assembly is found installed incorrectly during the inspection required by paragraph (k) of this AD: Before further flight, do the follow-on and corrective actions required by paragraph (i) of this AD. Credit for Actions Done Using Previous Service Information (m) Inspections and corrective actions done before the effective date of this AD in accordance with a Boeing service bulletin listed in Table 1 of this AD are acceptable for compliance with the corresponding requirements of this AD. TABLE 1—PREVIOUS SERVICE BULLETINS Boeing Alert Service Bulletin— Revision— Dated— 737–71A1462 ......................................................................................................................................................... 737–71A1462 ......................................................................................................................................................... 737–71A1462 ......................................................................................................................................................... Original .... 1 .............. 2 .............. August 29, 2002. November 7, 2002. May 29, 2003. erowe on DSK2VPTVN1PROD with RULES Parts Installation (n) As of the effective date of this AD, no person may install an engine on any airplane identified in paragraph (c) of this AD unless the actions required by paragraph (n)(1) or (n)(2) of this AD are accomplished. (1) The inspection is accomplished in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004, and the center link assembly of the aft engine mount is found to be installed correctly. (2) The hanger fitting and center link assembly are marked and part marked in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004. Note 3: For hanger fittings and center link assemblies marked and part marked in production, as specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004, the actions specified in paragraph (n)(2) of this AD do not apply. VerDate Mar<15>2010 14:42 Sep 30, 2011 Jkt 226001 Alternative Methods of Compliance (AMOCs) (o) The certification office specified in paragraph (o)(1) or (o)(2) of this AD, as applicable, has the authority to approve AMOCs for paragraphs (i) and (j) of this AD, if requested using the procedures found in 14 CFR 39.19. (1) For the structure identified in paragraph (i)(2) of this AD: The Manager, Engine Certification Office (ECO), FAA. Send information to ATTN: Antonio Cancelliere, Aerospace Engineer, ANE–141, FAA, ECO, 12 New England Executive Park, Burlington, Massachusetts 01803–5299; telephone 781– 238–7751; fax 781–238–7199. (2) For the structure identified in paragraph (i)(3) of this AD: The Manager, Seattle Aircraft Certification Office (ACO), FAA. Send information to ATTN: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM– 120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6450; fax (425) 917– 6590. Information may be e-mailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 (3) 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 appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (4) An AMOC that provides an acceptable level of safety may be used for any repair required by paragraph (i)(3) of this AD if it is approved by Boeing Commercial Airplanes Organization Designation Authorization (ODA) that 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. Material Incorporated by Reference (p) You must use Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated E:\FR\FM\03OCR1.SGM 03OCR1 61036 Federal Register / Vol. 76, No. 191 / Monday, October 3, 2011 / Rules and Regulations May 20, 2004, 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 Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004, 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 referenced 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. (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 an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington on September 8, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. Peter A. White, Manager, Engine and Propeller Directorate, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–24681 Filed 9–30–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Cracked nuts * * * were found on aircraft’s production line during routine post assembly inspection. Investigation revealed that the cracks resulted from hydrogen embrittlement combined with high hardness. Non-conformity with certified mechanical properties of this fastener can potentially lead to an unsafe condition. The unsafe condition is cracked nuts in multiple locations (including aileron fittings, rudder tab assembly and mounting structure for power drive units) could result in failure of affected locations and consequent reduced controllability or reduced structural capability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. This AD becomes effective November 7, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 7, 2011. ADDRESSES: You may examine the AD docket on the Internet at http:// 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: Mike Borfitz, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2677; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: Federal Aviation Administration Discussion 14 CFR Part 39 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 June 29, 2011 (76 FR 38062). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: [Docket No. FAA–2011–0646; Directorate Identifier 2010–NM–224–AD; Amendment 39–16814; AD 2011–20–04] RIN 2120–AA64 Airworthiness Directives; Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 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 product. The MCAI describes the unsafe condition as: erowe on DSK2VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 14:42 Sep 30, 2011 Jkt 226001 Cracked nuts (P/N [part number] MS– 21042L3) were found on aircraft’s production line during routine post assembly inspection. Investigation revealed that the cracks resulted from hydrogen embrittlement combined with high hardness. Nonconformity with certified mechanical properties of this fastener can potentially lead to an unsafe condition. The unsafe condition of cracked nuts in multiple locations (including aileron fittings, rudder tab assembly and mounting structure for power drive units) could result in failure of affected locations and consequent reduced controllability or reduced structural PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 capability of the airplane. The required actions include replacing nuts having P/N MS21042L3, and in certain locations, a one time radiographic inspection for cracked nuts and replacing any cracked nuts. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (76 FR 38062, June 29, 2011) or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 2 products of U.S. registry. We also estimate that it will take about 227 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $0 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $38,590, or $19,295 per product. 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 E:\FR\FM\03OCR1.SGM 03OCR1

Agencies

[Federal Register Volume 76, Number 191 (Monday, October 3, 2011)]
[Rules and Regulations]
[Pages 61033-61036]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-24681]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 76, No. 191 / Monday, October 3, 2011 / Rules 
and Regulations

[[Page 61033]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1118; Directorate Identifier 2007-NM-318-AD; 
Amendment 39-16792; AD 2011-18-10]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. The existing AD currently requires 
reviewing the airplane maintenance records to determine whether an 
engine has been removed from the airplane since the airplane was 
manufactured. For airplanes on which an engine has been removed, the 
existing AD also requires an inspection of the aft engine mount to 
determine if the center link assembly is correctly installed, and 
follow-on actions if necessary. This new AD expands the applicability 
to include airplanes on which the engine has not been previously 
removed, and Model 737-900ER airplanes. This AD was prompted by reports 
indicating that operators found that the center link assembly for the 
aft engine mount was reversed on several airplanes that had not had an 
engine removed since delivery. We are issuing this AD to prevent 
increased structural loads on the aft engine mount, which could result 
in failure of the aft engine mount and consequent separation of the 
engine from the airplane.

DATES: This AD is effective November 7, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of November 7, 
2011.

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. You may review copies of the 
referenced 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 (phone: 800-647-5527) is 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: Alan Pohl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6450; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede airworthiness directive (AD) 2003-03-
01, Amendment 39-13025 (68 FR 4367, January 29, 2003). That AD applies 
to the specified products. The SNPRM published in the Federal Register 
on January 11, 2011 (76 FR 1552). The original NPRM (73 FR 64568, 
October 30, 2008) proposed to continue to require reviewing the 
airplane maintenance records to determine whether an engine has been 
removed from the airplane since the airplane was manufactured. For 
airplanes on which an engine has been removed, the original NPRM also 
requires an inspection of the aft engine mount to determine if the 
center link assembly is correctly installed, and follow-on actions if 
necessary. The original NPRM also proposed to require those same 
actions on airplanes on which the engine has not previously been 
removed. The SNPRM proposed to further expand the applicability to 
include Model 737-900ER airplanes.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Supportive Comments

    Boeing and Continental Airlines concur with the SNPRM (76 FR 1552, 
January 11, 2011).

Request for Information

    American Airlines stated that it has accomplished the actions 
required by AD 2003-03-01 (68 FR 4367, January 29, 2003) and the SNPRM 
(76 FR 1552, January 11, 2011), and although it will no longer be 
affected by the requirements in the SNPRM, asked the following 
questions:
     What action has the original equipment manufacturer, 
Boeing, taken to prevent incorrect aft mount assembly installations?
     Can Boeing specifically identify the procedures and/or 
best practices incorporated into their production process to prevent a 
recurrence of this type of event?
    We acknowledge the commenter's concerns and provide the following 
responses:
     Boeing Alert Service Bulletin 737-71A1462, Revision 2, 
dated May 29, 2003; and Revision 3, dated May 20, 2004; specify marking 
of the hangar fitting (pylon structure) and center link (engine 
structure) assembly, which is the same as the marking incorporated 
previously in production. These marks ``L,'' ``AFT,'' and ``R,'' 
applied to both the hangar fitting and center link assembly will only 
be in close proximity if the center link is installed correctly.
     Boeing has advised us that it has revised the instructions 
in its component maintenance manuals

[[Page 61034]]

(assembly level) and aircraft maintenance manuals (installation level) 
to put special emphasis on the center link installation. Boeing also 
advised us that it implemented drawing changes affecting both 
production assembly and field installation of this part; these changes 
incorporated specific markings on both the center link assembly and the 
hanger fitting to which it is attached. Boeing noted that after 2003 
the parts were marked with an ``L'' and ``R'' (left and right) to 
indicate the part orientation when assembled, and the hanger assembly 
was marked with `AFT' at the center line. Boeing has also developed a 
shop aid for use at the facility where the parts are fabricated and 
assembled which helps the assembler confirm the correct orientation of 
the parts. We have made no change to the AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.

Costs of Compliance

    We estimate that this AD affects 854 airplanes of U.S. registry. 
There are no new requirements in this AD; however, we have expanded the 
applicability of this AD. The current costs for this AD are 
recalculated for the convenience of affected operators, as follows:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per
                     Action                         Work hours         Parts         airplane       Fleet cost
----------------------------------------------------------------------------------------------------------------
Maintenance records review (required by AD 2003-               1              $0             $85         $72,590
 03-01, Amendment 39-13025 (68 FR 4367, January
 29, 2003)).....................................
Inspection for correct installation of center                  1               0              85          72,590
 link assembly (new required action)............
----------------------------------------------------------------------------------------------------------------

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

    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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

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 FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2003-03-01, Amendment 39-13025 (68 FR 4367, January 29, 2003), and by 
adding the following new AD:

2011-18-10 The Boeing Company: Amendment 39-16792; Docket No. FAA-
2008-1118; Directorate Identifier 2007-NM-318-AD.

Effective Date

    (a) This AD is effective November 7, 2011.

Affected ADs

    (b) This AD supersedes AD 2003-03-01, Amendment 39-13025 (68 FR 
4367, January 29, 2003).

Applicability

    (c) This AD applies to all The Boeing Company Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes, certificated in 
any category.

Subject

    (d) Air Transport Association (ATA) of America Code 71: 
Powerplant.

Unsafe Condition

    (e) This AD was prompted by reports indicating that operators 
found that the center link assembly for the aft engine mount was 
reversed on several airplanes that had not had an engine removed 
since delivery. We are issuing this AD to prevent increased 
structural loads on the aft engine mount, which could result in 
failure of the aft engine mount and consequent separation of the 
engine from the airplane.

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.

Restatement of Requirements of AD 2003-03-01 (68 FR 4367, January 29, 
2003): Review of Maintenance Records

    (g) For Model 737-600, -700, -700C, -800, and -900 series 
airplanes: Within 90 days after February 13, 2003 (the effective 
date of AD 2003-03-01 (68 FR 4367, January 29, 2003)), review the 
airplane maintenance records to determine whether either engine has 
been removed since the airplane's date of manufacture. If neither 
engine has been removed since the airplane's date of manufacture, no 
further action is required by this paragraph.

Inspection of Engines That Have Been Removed To Determine If Center 
Link Assembly Is Installed Correctly

    (h) For Model 737-600, -700, -700C, -800, and -900 series 
airplanes on which any installed engine has been removed from the 
airplane since the airplane's date of manufacture: Within 90 days 
after February 13, 2003, do a one-time general visual inspection to 
determine if the center link

[[Page 61035]]

assembly of the aft engine mount is installed correctly, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-71A1462, Revision 1, dated November 7, 2002; or 
Revision 3, dated May 20, 2004. If the center link assembly is 
installed correctly, no further action is required by paragraph (h) 
or (i) of this AD for that engine. As of the effective date of this 
AD, use only Boeing Alert Service Bulletin 737-71A1462, Revision 3, 
dated May 20, 2004.


    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, hanger 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.''

Follow-On and Corrective Actions

    (i) For airplanes on which any center link assembly is found 
installed incorrectly during any inspection required by paragraph 
(h), (k), or (l) of this AD: Before further flight, do the actions 
specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-71A1462, Revision 1, dated November 7, 2002; or 
Revision 3, dated May 20, 2004; except that it is not necessary to 
submit a report of findings to the airplane manufacturer. As of the 
effective date of this AD, use only Boeing Alert Service Bulletin 
737-71A1462, Revision 3, dated May 20, 2004.
    (1) Remove the center link assembly and install it correctly.
    (2) Perform a detailed inspection of the engine mounting lugs 
and engine turbine rear frame for cracking, yielding, buckling, or 
wear damage.
    (3) Perform a detailed inspection of the hardware for the aft 
engine mount; including the center link assembly, right link 
assembly, aft mount hanger assembly, and link pins; for cracking, 
yielding, buckling, or wear damage.


    Note 2: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Repair

    (j) If any cracking, yielding, buckling, or wear damage is found 
during the inspections required by paragraphs (i)(2) and (i)(3) of 
this AD: Before further flight, replace the discrepant part with a 
new or serviceable part, or repair in accordance with a method 
approved in accordance with the procedures specified in paragraph 
(o) of this AD.

New Requirements of This AD

Inspection of Engines That Have Not Been Removed To Determine If Center 
Link Assembly Is Installed Correctly

    (k) For airplanes identified in Boeing Alert Service Bulletin 
737-71A1462, Revision 3, dated May 20, 2004, on which any installed 
engine has not been removed from the airplane since the airplane's 
date of manufacture: Within 90 days after the effective date of this 
AD, do a detailed inspection to determine if the center link 
assembly of the aft engine mount is installed correctly, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-71A1462, Revision 3, dated May 20, 2004. If the 
center link is installed correctly, no further action is required by 
this paragraph for that engine.

Follow-On and Corrective Actions

    (l) For airplanes on which any center link assembly is found 
installed incorrectly during the inspection required by paragraph 
(k) of this AD: Before further flight, do the follow-on and 
corrective actions required by paragraph (i) of this AD.

Credit for Actions Done Using Previous Service Information

    (m) Inspections and corrective actions done before the effective 
date of this AD in accordance with a Boeing service bulletin listed 
in Table 1 of this AD are acceptable for compliance with the 
corresponding requirements of this AD.

                   Table 1--Previous Service Bulletins
------------------------------------------------------------------------
Boeing Alert Service Bulletin--
                                  Revision--             Dated--
------------------------------------------------------------------------
737-71A1462...................  Original......  August 29, 2002.
737-71A1462...................  1.............  November 7, 2002.
737-71A1462...................  2.............  May 29, 2003.
------------------------------------------------------------------------

Parts Installation

    (n) As of the effective date of this AD, no person may install 
an engine on any airplane identified in paragraph (c) of this AD 
unless the actions required by paragraph (n)(1) or (n)(2) of this AD 
are accomplished.
    (1) The inspection is accomplished in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004, and the center link 
assembly of the aft engine mount is found to be installed correctly.
    (2) The hanger fitting and center link assembly are marked and 
part marked in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-71A1462, Revision 
3, dated May 20, 2004.


    Note 3: For hanger fittings and center link assemblies marked 
and part marked in production, as specified in Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004, the actions specified in 
paragraph (n)(2) of this AD do not apply.

Alternative Methods of Compliance (AMOCs)

    (o) The certification office specified in paragraph (o)(1) or 
(o)(2) of this AD, as applicable, has the authority to approve AMOCs 
for paragraphs (i) and (j) of this AD, if requested using the 
procedures found in 14 CFR 39.19.
    (1) For the structure identified in paragraph (i)(2) of this AD: 
The Manager, Engine Certification Office (ECO), FAA. Send 
information to ATTN: Antonio Cancelliere, Aerospace Engineer, ANE-
141, FAA, ECO, 12 New England Executive Park, Burlington, 
Massachusetts 01803-5299; telephone 781-238-7751; fax 781-238-7199.
    (2) For the structure identified in paragraph (i)(3) of this AD: 
The Manager, Seattle Aircraft Certification Office (ACO), FAA. Send 
information to ATTN: Alan Pohl, Aerospace Engineer, Airframe Branch, 
ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 917-6450; fax (425) 917-6590. 
Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (3) 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 appropriate principal inspector, or lacking a 
principal inspector, the manager of the local flight standards 
district office/certificate holding district office. The AMOC 
approval letter must specifically reference this AD.
    (4) An AMOC that provides an acceptable level of safety may be 
used for any repair required by paragraph (i)(3) of this AD if it is 
approved by Boeing Commercial Airplanes Organization Designation 
Authorization (ODA) that 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.

Material Incorporated by Reference

    (p) You must use Boeing Alert Service Bulletin 737-71A1462, 
Revision 3, dated

[[Page 61036]]

May 20, 2004, 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 Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004, 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 referenced 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.
    (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 an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington on September 8, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
Peter A. White,
Manager, Engine and Propeller Directorate, Engine and Propeller 
Directorate, Aircraft Certification Service.
[FR Doc. 2011-24681 Filed 9-30-11; 8:45 am]
BILLING CODE 4910-13-P