Airworthiness Directives; The Boeing Company Airplanes, 14977-14982 [2014-04819]

Download as PDF 14977 Rules and Regulations Federal Register Vol. 79, No. 52 Tuesday, March 18, 2014 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–2013–0542; Directorate Identifier 2011–NM–162–AD; Amendment 39–17785 AD 2014–05–12] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2010–15– 08 for all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. AD 2010–15–08 required repetitive inspections for discrepancies of each carriage spindle of the outboard mid-flaps; repetitive gap checks of the inboard and outboard carriages of the outboard mid-flaps to detect fractured carriage spindles; measuring to ensure that any new or serviceable carriage spindle meets minimum allowable diameter measurements taken at three locations; repetitive inspections, measurements, and overhaul of the carriage spindles; replacement of any carriage spindle when it has reached its maximum life limit; and corrective actions if necessary. This new AD requires reducing the life limit of the carriages, reducing the repetitive interval for certain inspections and gap checks for certain carriages. This new AD also adds an option, for certain replacements, of doing an inspection, and related investigative and corrective actions if necessary. This AD was prompted by a report of failure of both flap carriages. We are issuing this AD to detect and correct cracked, corroded, or fractured carriage spindles, which could lead to severe flap asymmetry, and could result sroberts on DSK5SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 17:18 Mar 17, 2014 Jkt 232001 in reduced control or loss of controllability of the airplane. DATES: This AD is effective April 22, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 22, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 31, 2010 (75 FR 43803, July 27, 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; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 by searching for and locating Docket No. FAA–2014–05– 12 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 Docket 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 (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917– 6440; fax: (425) 917–6590; email: nancy.marsh@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2010–15–08, Amendment 39–16374 (75 FR 43803, PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 July 27, 2010). AD 2010–15–08 applied to all The Boeing Company Model 737– 100, –200, –200C, –300, –400, and –500 series airplanes. The NPRM published in the Federal Register on July 1, 2013 (78 FR 39193). The NPRM was prompted by a report of failure of both flap carriages. The NPRM proposed to continue to require repetitive inspections for discrepancies of each carriage spindle of the outboard midflaps; repetitive gap checks of the inboard and outboard carriages of the outboard mid-flaps to detect fractured carriage spindles; measuring to ensure that any new or serviceable carriage spindle meets minimum allowable diameter measurements taken at three locations; repetitive inspections, measurements, and overhaul of the carriage spindles; replacement of any carriage spindle when it has reached its maximum life limit; and corrective actions if necessary. The NPRM also proposed to require reducing the life limit of the carriages, reducing the repetitive interval for certain inspections and gap checks for certain carriages. The NPRM also proposed to add an option, for certain replacements, of doing an inspection, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracked, corroded, or fractured carriage spindles, which could lead to severe flap asymmetry, and could result in reduced control or loss of controllability of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (78 FR 39193, July 1, 2013) and the FAA’s response to each comment. Request to Revise Note Boeing requested we revise note 1 to paragraph (m) of the NPRM (78 FR 39193, July 1, 2013) to read, ‘‘. . . Boeing (737) Standard Overhaul Practices Manual (SOPM), Revision 25 or later.’’ Boeing stated that as its production standard changes, the SOPM is revised each time the SOPM is updated. Boeing stated that a global alternative method of compliance (AMOC) is required each time the SOPM is revised and this generates AMOC activity that does not enhance fleet safety. E:\FR\FM\18MRR1.SGM 18MRR1 14978 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations We disagree to revise Note 1 to paragraph (m) of this final rule because the text in Note 1 is informational guidance and does not relieve the requirement in paragraph (m) to obtain approval for the method used to apply plating, regardless of what revision of the SOPM is specified. We have not changed this final rule in this regard. Request to Revise Requirement for Plating Boeing requested the following requirement in paragraph (m)(3) of the NPRM (78 FR 39193, July 1, 2013) be removed, ‘‘The carriage must not be plated using any high velocity oxygen fuel (HVOF) thermal spray process.’’ Boeing stated AD 2011–04–10, Amendment 39–16609 (76 FR 9498, February 18, 2011), and AD 2012–13– 07, Amendment 39–17109 (77 FR 39153, July 2, 2012), required diligent inspection of HVOF coated carriages. Boeing stated that inspections to date have only found minor corrosion, well in advance of a potential unsafe condition. Boeing stated requiring carriages to be converted to nickel [plating] does not enhance fleet safety. We disagree to remove the requested phrase. The restriction against future application of HVOF plating of the flap carriages was coordinated and agreed to by The Boeing Company prior to issuance of the NPRM (78 FR 39193, July 1, 2013). Service experience has shown that the HVOF coating has insufficient reliability, therefore the restriction is necessary. We have not changed this final rule in this regard. Federal Aviation Regulations (14 CFR 39.17). We have redesignated paragraph (c) of the NPRM (78 FR 39193, July 1, 2013) as (c)(1) and added this provision in new paragraph (c)(2) of this final rule. Clarification Regarding the Installation of Winglets Aviation Partners Boeing (APB) stated the installation of winglets per Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/ rgstc.nsf/0/BE866B732F6CF31086257B 9700692796?Open Document&Highlight=st01219se) does not affect the accomplishment of the manufacturer’s service instructions. We agree with APB’s statement that the installation of winglets as specified in STC ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/ rgstc.nsf/0/BE866B732F6CF31086257B 9700692796?Open Document&Highlight=st01219se) does not affect accomplishment of the requirements of this AD, and for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ (AMOC) approval request is not necessary to comply with the requirements of section 39.17 of the We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 39193, July 1, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 39193, July 1, 2013). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Conclusion Costs of Compliance We estimate that this AD affects 652 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspections [actions retained from existing AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)]. Inspections and measurements [actions retained from existing AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)]. Overhauls [actions retained from existing AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)]. Replacements [actions retained from existing AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)]. 12 work-hours × $85 per hour = $1,020. $0 $1,020 per inspection cycle. $665,040 per inspection cycle. 2 work-hours × $85 per hour = $170. $0 $170 per inspection and measurement cycle. 1 $7,000 Parts cost Cost per product Cost on U.S. operators 16 work-hours × $85 per hour = $1,360. 1 $28,000 $29,360 per overhaul cycle. $110,840 per inspection and measurement cycle. $19,142,720 per overhaul cycle. 16 work-hours × $85 per hour = $1,360. 2 $60,000 $61,360 per replacement cycle. $40,006,720 per replacement cycle. per spindle; 4 spindles per airplane. per spindle; 4 spindles per airplane. 2 $15,000 The new requirements of this AD add no additional economic burden. sroberts on DSK5SPTVN1PROD with RULES 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, VerDate Mar<15>2010 17:18 Mar 17, 2014 Jkt 232001 ‘‘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. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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, E:\FR\FM\18MRR1.SGM 18MRR1 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations (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 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) 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), and adding the following new AD: ■ 2014–05–12 The Boeing Company: Amendment 39–17785; Docket No. FAA–2013–0542; Directorate Identifier 2011–NM–162–AD. (a) Effective Date This AD is effective April 22, 2014. sroberts on DSK5SPTVN1PROD with RULES (b) Affected ADs This AD supersedes AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010). (c) Applicability (1) This AD applies to all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/BE866B732F6CF31086257 B9700692796?OpenDocument& Highlight=st01219se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 57: Wings. VerDate Mar<15>2010 17:18 Mar 17, 2014 Jkt 232001 14979 (e) Unsafe Condition This AD was prompted by a report of failure of both flap carriages. We are issuing this AD to detect and correct cracked, corroded, or fractured carriage spindles, which could lead to severe flap asymmetry, and could result in reduced control or loss of controllability of the airplane. doing the next gap check may be measured from the NDT inspection. (2) As carriage spindles gain flight cycles or years in service and move from one category in the ‘‘Threshold’’ column to another, they are subject to the repetitive inspection intervals corresponding to the new threshold category. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (h) Retained Work Package 2: Gap Check This paragraph restates the requirements of paragraph (h) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information. Perform a gap check of the inboard and outboard carriage of the left and right outboard mid-flaps to determine if there is a positive indication of a severed carriage spindle, in accordance with Work Package 2 of paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012. As of the effective date of this AD, only Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012, may be used to perform the actions specified in this paragraph. (g) Compliance Times for Paragraphs (h) and (j) of This AD This paragraph restates the requirements of paragraph (g) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information that shortens the compliance times for certain inspections. The tables in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003; and Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012; specify the compliance times for paragraphs (g) through (k) of this AD. For carriage spindles that have accumulated the number of flight cycles or years in service specified in the ‘‘Threshold’’ column of the tables in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003, accomplish the gap check, nondestructive test (NDT) inspection, and general visual inspection specified in paragraphs (h) and (j) of this AD within the corresponding interval after December 4, 2003 (the effective date AD 2003–24–08, Amendment 39–13337 (68 FR 67027, December 1, 2003)), as specified in the ‘‘Interval’’ column of the tables in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003, except as specified in paragraph (g)(1) or (g)(2) of this AD. Repeat the gap check, NDT, and general visual inspections at the intervals specified in the ‘‘Interval’’ column of the tables in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003, except as specified in paragraph (g)(1) and (g)(2) of this AD. As of the effective date of this AD, accomplish the gap check, NDT inspection, and general visual inspections specified in paragraphs (h) and (j) of this AD within the corresponding interval as specified in the ‘‘Interval’’ column of the tables in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003, and thereafter at the intervals specified in Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012, except as specified in paragraphs (g)(1) and (g)(2) of this AD. Repeat the gap check, NDT, and general visual inspections thereafter at the intervals specified in the ‘‘Interval’’ column of the tables in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012, except as specified in paragraphs (g)(1) and (g)(2) of this AD. (1) The gap check does not have to be done at the same time as an NDT inspection; after doing an NDT inspection, the interval for PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 (i) Retained Work Package 2: Corrective Actions with New Optional Actions and Exception This paragraph restates the requirements of paragraph (i) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information and new optional actions and exception. If there is a positive indication of a severed carriage spindle during the gap check required by paragraph (h) of this AD, before further flight, do the actions specified in paragraph (i)(1) or (i)(2) of this AD, except for carriage spindles on which an ultrasonic inspection has been done in accordance with the ‘‘Work Instructions’’ of Boeing Service Bulletin 737– 57A1277, Revision 3, dated May 16, 2012; and the spindle has been confirmed not to be severed, no further actions are required by this paragraph for that carriage spindle. (1) Remove the carriage spindle and install a new or serviceable carriage spindle, in accordance with the ‘‘Work Instructions’’ of any service bulletin specified in paragraph (i)(1)(i), (i)(1)(ii), (i)(1)(iii), or (i)(1)(iv) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012, may be used to perform the actions specified in this paragraph. (i) Boeing Alert Service Bulletin 737– 57A1277, Revision 1, dated November 25, 2003. (ii) Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012. (iii) Boeing Alert Service Bulletin 737– 57A1218, Revision 5, dated February 9, 2009. (iv) Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011. (2) Do a detailed inspection of the spindle to determine if there is corrosion, cracking, or a severed spindle, and, before further flight, do all related investigative and corrective actions, in accordance with the ‘‘Work Instructions’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003; or Boeing Service E:\FR\FM\18MRR1.SGM 18MRR1 14980 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations Bulletin 737–57A1277, Revision 3, dated May 16, 2012. If, during the detailed inspection described in paragraph 4.b. of Work Package 2 of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003; or Boeing Alert Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012; a carriage spindle is found not to be severed, and no corrosion and no cracking is present, it can be reinstalled on the outboard mid-flap, in accordance with any service bulletin specified in paragraph (i)(2)(i), (i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012, may be used to perform the actions specified in this paragraph. (i) Boeing Alert Service Bulletin 737– 57A1277, Revision 1, dated November 25, 2003. (ii) Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012. (iii) Boeing Alert Service Bulletin 737– 57A1218, Revision 5, dated February 9, 2009. (iv) Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011. sroberts on DSK5SPTVN1PROD with RULES (j) Retained Work Package 1: NDT (Ultrasonic) and General Visual Inspections This paragraph restates the requirements of paragraph (j) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information. Perform an NDT (ultrasonic) inspection and general visual inspection for each carriage spindle of the left and right outboard mid-flaps to detect cracks, corrosion, or severed carriage spindles, in accordance with ‘‘Work Package 1’’ of the ‘‘Work Instructions’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012. As of the effective date of this AD, only Boeing Service Bulletin 737– 57A1277, Revision 3, dated May 16, 2012, may be used to perform the actions specified in this paragraph. (k) Retained Work Package 1: Corrective Actions and New Optional Action This paragraph restates the requirements of paragraph (k) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information and new optional action. If any corroded, cracked, or severed carriage spindle is found during any inspection required by paragraph (j) of this AD: Before further flight, do the actions specified in paragraph (k)(1) or (k)(2) of this AD. (1) Remove the carriage spindle and install a new or serviceable carriage spindle, in accordance with any service bulletin identified in paragraph (k)(1)(i), (k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012, may be used to perform the actions specified in this paragraph. (i) Boeing Alert Service Bulletin 737– 57A1277, Revision 1, dated November 25, 2003. (ii) Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012. (iii) Boeing Alert Service Bulletin 737– 57A1218, Revision 5, dated February 9, 2009. VerDate Mar<15>2010 17:18 Mar 17, 2014 Jkt 232001 (iv) Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011. (2) Do a detailed inspection of the spindle to determine if there is corrosion, cracking, or a severed spindle, in accordance with the ‘‘Work Instructions’’ of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012. If any corrosion, cracking, or a severed spindle is found, before further flight, install a new or serviceable carriage spindle, in accordance with any service bulletin identified in paragraph (k)(1)(i), (k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012, may be used to perform the actions specified in this paragraph. (l) Retained Parts Installation Limitation This paragraph restates the requirements of paragraph (l) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010). Except as provided by paragraph (i) of this AD: As of December 4, 2003 (the effective date AD 2003–24–08, Amendment 39–13337 (68 FR 67027, December 1, 2003)), no person may install on any airplane a carriage spindle that has been removed as required by paragraph (i) or (k) of this AD, unless it has been overhauled in accordance with the ‘‘Work Instructions’’ of the applicable service bulletin identified in paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012; or Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011; may be used to perform the actions specified in this paragraph. To be eligible for installation under this paragraph, the carriage spindle must have been overhauled in accordance with the requirements of paragraph (m) of this AD. (1) Boeing Alert Service Bulletin 737– 57A1277, Revision 1, dated November 25, 2003. (2) Boeing Service Bulletin 737–57A1277, Revision 3, dated May 16, 2012. (3) Boeing Alert Service Bulletin 737– 57A1218, Revision 5, dated February 9, 2009. (4) Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011. (m) Retained Electrodeposited Nickel Plating With New Plating Restrictions This paragraph restates the requirements of paragraph (m) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010) with revised plating application procedures. As of the effective date of this AD, during accomplishment of any overhaul specified in paragraph (l) or (o) of this AD, follow the requirements specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD during application of the plating to the carriage spindle, in accordance with a method approved by the Manager, Seattle, Aircraft Certification Office (ACO), FAA. 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. (1) The maximum deposition rate of the nickel plating in any one plating/baking cycle must not exceed 0.002-inch-per-hour. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (2) Begin the hydrogen embrittlement relief bake within 10 hours after application of the nickel plating, or less than 24 hours after the current was first applied to the part, whichever is first. (3) The carriage must not be plated using any high velocity oxygen fuel (HVOF) thermal spray process. Note 1 to paragraph (m) of this AD: Guidance on the application of nickel plating can be found in Chapter 20–42–09, Electrodeposited Nickel Plating, of the Boeing (737) Standard Overhaul Practices Manual, Revision 25, dated July 1, 2009. (n) Retained Exception to Reporting Recommendations This paragraph restates the provisions of paragraph (n) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information. Although Boeing Alert Service Bulletin 737– 57A1277, Revision 1, dated November 25, 2003; and Boeing Service Bulletin 737– 57A1277, Revision 3, dated May 16, 2012; recommend that operators report inspection findings to the manufacturer, this AD does not require reporting. (o) Retained Inspections, Measurements, and Overhauls of the Carriage Spindle With Clarification of Overhaul Restrictions This paragraph restates the requirements of paragraph (o) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010) with clarification of overhaul restrictions. At the applicable times specified in paragraphs (o)(1) and (o)(2) of this AD: Do the detailed inspection for corrosion, pitting, and cracking of the carriage spindle; magnetic particle inspection for cracking of the carriage spindle; measurements of the spindle to determine if it meets the allowable minimum diameter; overhauls of the carriage spindle; and applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–57A1218, Revision 5, dated February 9, 2009; or Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011. As of the effective date of this AD, only Boeing Alert Service Bulletin 737–57A1218, Revision 6, dated June 9, 2011, may be used to perform the actions specified in this paragraph. The applicable corrective actions must be done before further flight. Repeat these actions thereafter at intervals not to exceed every 12,000 flight cycles on the carriage spindle or every 8 years since first installation of the carriage spindle on the airplane, whichever comes first. As of the effective date of this AD: For any overhaul required by this paragraph, the carriage spindle must be overhauled in accordance with the requirements of paragraph (m) of this AD. (1) For Model 737–100, -200, -200C series airplanes: At the later of the times specified in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD. (i) Before the accumulation of 12,000 total flight cycles on the carriage spindle since new or overhauled, or within 8 years after the installation of the new or overhauled part, whichever comes first. (ii) Within 1 year after August 31, 2010 (the effective date of AD 2010–15–08, E:\FR\FM\18MRR1.SGM 18MRR1 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations Amendment 39–16374 (75 FR 43803, July 27, 2010)). (2) For Model –300, –400, and –500 series airplanes: At the later of the times specified in paragraphs (o)(2)(i) and (o)(2)(ii) of this AD. (i) Before the accumulation of 12,000 total flight cycles on the carriage spindle since new or overhauled, or within 8 years after the installation of the new or overhauled part, whichever comes first. (ii) Within 2 years after August 31, 2010 (the effective date of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)). sroberts on DSK5SPTVN1PROD with RULES (p) Retained Carriage Spindle Replacement for Model 737–100, –200, and –200C Series Airplanes This paragraph restates the requirements of paragraph (p) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information and a shortened compliance time. For Model 737–100, –200, –200C series airplanes: Replace the carriage spindle with a new or documented (for which the service life, in total flight cycles, is known) carriage spindle, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–57A1218, Revision 5, dated February 9, 2009; or Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011; at the earlier of the times specified in paragraphs (p)(1) and (p)(2) of this AD, except as required by paragraph (r) of this AD. As of the effective date of this AD, only Boeing Alert Service Bulletin 737–57A1218, Revision 6, dated June 9, 2011, may be used to perform the replacement. Overhauling the carriage spindles does not zero-out the flight cycles. Total flight cycles accumulate since new. (1) At the later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this AD. (i) Before the accumulation of 48,000 total flight cycles on the new or overhauled carriage. (ii) Within 3 years or 7,500 flight cycles after August 31, 2010 (the effective date of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)), whichever occurs first. (2) Before the accumulation of 40,000 total flight cycles on the new or overhauled carriage or 6 months after the effective date of this AD, whichever occurs later. (q) Retained Carriage Spindle Replacement for Model 737–300, –400, and –500 Series Airplanes This paragraph restates the requirements of paragraph (q) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised service information and a shortened compliance time. For Model 737–300, –400, and –500 series airplanes: Replace the carriage spindle with a new or documented (for which the service life, in flight cycles, is known) carriage spindle, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–57A1218, Revision 5, dated February 9, 2009; or Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011; at the later of the times specified in paragraphs VerDate Mar<15>2010 17:18 Mar 17, 2014 Jkt 232001 (q)(1) and (q)(2) of this AD, except as required by paragraph (r) of this AD. As of the effective date of this AD, only Boeing Alert Service Bulletin 737–57A1218, Revision 6, dated June 9, 2011, may be used to perform the replacement required by this paragraph. Overhauling the carriage spindles does not zero-out the flight cycles. Total flight cycles accumulate since new. (1) Before the accumulation of 40,000 total flight cycles on the new or overhauled carriage. (2) Within 6 years or 15,000 flight cycles after August 31, 2010 (the effective date of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)), whichever occurs first. (r) Retained Carriage Spindle Replacement for Airplanes With an Undocumented Carriage This paragraph restates the requirements of paragraph (r) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010). For airplanes with an undocumented carriage: Do the applicable actions specified in paragraph (p) or (q) of this AD at the applicable time specified in paragraph (r)(1) or (r)(2) of this AD. (1) For Model 737–100, –200, –200C series airplanes: Do the actions specified in paragraph (p) of this AD at the time specified in paragraph (p)(1)(ii) of this AD. (2) For Model –300, –400, and –500 series airplanes: Do the actions specified in paragraph (q) of this AD at the time specified in paragraph (q)(2) of this AD. (s) Retained Repetitive Replacements of Carriage Spindle This paragraph restates the requirements of paragraph (s) of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), with revised compliance times. (1) For airplanes on which the actions required by paragraph (p) or (q) of this AD, as applicable, have been done as of the effective date of this AD: Repeat the replacement of the carriage spindle specified by paragraph (p) or (q) of this AD, as applicable, one time at the later of the times specified in paragraphs (s)(1)(i) and (s)(1)(ii) of this AD, and thereafter at intervals not to exceed 40,000 total flight cycles on the new or overhauled carriage spindle. (i) Before the accumulation of 40,000 total flight cycles on the new or overhauled carriage. (ii) Within 6 years or 15,000 flight cycles after August 31, 2010 (the effective date of AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010)), whichever occurs first. (2) For airplanes on which the actions required by paragraph (p) or (q) of this AD, as applicable, have not been done as of the effective date of this AD: Repeat the replacement of the carriage spindle specified by paragraph (p) or (q) of this AD, as applicable, thereafter at intervals not to exceed 40,000 total flight cycles on the new or overhauled carriage spindle. (t) Exception to Compliance Time Where Boeing Service Bulletin 737– 57A1277, Revision 3, dated May 16, 2012, and Boeing Alert Service Bulletin 737– PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 14981 57A1218, Revision 6, dated June 9, 2011, specify a compliance time after the dates of those service bulletins, this AD requires compliance within the specified compliance time after the effective date of this AD. (u) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) through (s) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737–57A1277, Revision 2, dated June 9, 2011, which is not incorporated by reference in this AD. (v) Alternative Methods of Compliance (AMOCs) (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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (w) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, 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. (4) AMOCs previously approved in accordance with AD 2003–24–08, Amendment 39–13377 (68 FR 67027, December 1, 2003), or AD 2010–15–08, Amendment 39–16374 (75 FR 43803, July 27, 2010), are approved as AMOCs for individual repairs are acceptable for compliance with the corresponding provisions of this AD. All other existing AMOCs are not acceptable. (w) Related Information (1) For more information about this AD, contact Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917–6440; fax: (425) 917–6590; email: nancy.marsh@faa.gov. (2) Service information identified in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (x)(5) and (x)(6) of this AD. (x) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. E:\FR\FM\18MRR1.SGM 18MRR1 14982 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations (3) The following service information was approved for IBR on April 22, 2014. (i) Boeing Alert Service Bulletin 737– 57A1218, Revision 6, dated June 9, 2011. (ii) Boeing Alert Service Bulletin 737– 57A1277, Revision 3, dated May 16, 2012. (4) The following service information was approved for IBR on August 31, 2010 (75 FR 43803, July 27, 2010). (i) Boeing Alert Service Bulletin 737– 57A1218, Revision 5, dated February 9, 2009. (ii) Boeing Alert Service Bulletin 737– 57A1277, Revision 1, dated November 25, 2003. (5) For Boeing 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; Internet https:// www.myboeingfleet.com. (6) You may view this service information at 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. (7) You may view this 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on February 18, 2014. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–04819 Filed 3–17–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0326; Directorate Identifier 2012–NM–089–AD; Amendment 39–17786; AD 2014–05–13] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2004–12– 07 for certain The Boeing Company Model 757 series airplanes equipped with Rolls-Royce RB211 engines. AD 2004–12–07 required modification of the nacelle strut and wing structure; and for certain airplanes, repetitive detailed inspections of certain aft bulkhead fasteners for loose or missing fasteners, and corrective action if necessary. For sroberts on DSK5SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 17:18 Mar 17, 2014 Jkt 232001 certain other airplanes, AD 2004–12–07 required a one-time detailed inspection of the middle gusset of the inboard side load fitting for proper alignment, and realignment if necessary; a one-time eddy current inspection of certain fastener holes for cracking, and repair if necessary; and a detailed inspection of certain fasteners for loose or missing fasteners, and replacement with new fasteners if necessary. This new AD specifies a maximum compliance time limit. This AD was prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. We are issuing this AD to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut. DATES: This AD is effective April 22, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of April 22, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of July 21, 2004 (69 FR 33561, June 16, 2004). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of January 3, 2000 (64 FR 66370, November 26, 1999). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766–5680; Internet: https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 by searching for and locating Docket No. FAA–2013– 0326; 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 Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6440; fax: 425–917–6590; email: Nancy.Marsh@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004–12–07, Amendment 39–13666 (69 FR 33561, June 16, 2004). AD 2004–12–07 applied to certain The Boeing Company Model 757 series airplanes equipped with Rolls-Royce RB211 engines. The NPRM published in the Federal Register on April 15, 2013 (78 FR 22215). The NPRM was prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. The NPRM proposed to retain the requirements of AD 2004–12–07, which required modification of the nacelle strut and wing structure; and for certain airplanes, repetitive detailed inspections of certain aft bulkhead fasteners for loose or missing fasteners, and corrective action if necessary. For certain other airplanes, AD 2004–12–07 required a one-time detailed inspection of the middle gusset of the inboard side load fitting for proper alignment, and realignment if necessary; a one-time eddy current inspection of certain fastener holes for cracking, and repair if necessary; and a detailed inspection of certain fasteners for loose or missing fasteners, and replacement with new fasteners if necessary. The NPRM proposed to specify a maximum compliance time limit to modify the nacelle strut and wing structure. We are issuing this AD to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (78 FR 22215, April 15, 2013) and the FAA’s response to each comment. Support for the NPRM (78 FR 22215, April 15, 2013) Boeing stated that it concurs with the contents of the NPRM (78 FR 22215, April 15, 2013). E:\FR\FM\18MRR1.SGM 18MRR1

Agencies

[Federal Register Volume 79, Number 52 (Tuesday, March 18, 2014)]
[Rules and Regulations]
[Pages 14977-14982]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04819]



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                                                Federal Register
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Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules 
and Regulations

[[Page 14977]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0542; Directorate Identifier 2011-NM-162-AD; 
Amendment 39-17785 AD 2014-05-12]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2010-15-08 for 
all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. AD 2010-15-08 required repetitive inspections for 
discrepancies of each carriage spindle of the outboard mid-flaps; 
repetitive gap checks of the inboard and outboard carriages of the 
outboard mid-flaps to detect fractured carriage spindles; measuring to 
ensure that any new or serviceable carriage spindle meets minimum 
allowable diameter measurements taken at three locations; repetitive 
inspections, measurements, and overhaul of the carriage spindles; 
replacement of any carriage spindle when it has reached its maximum 
life limit; and corrective actions if necessary. This new AD requires 
reducing the life limit of the carriages, reducing the repetitive 
interval for certain inspections and gap checks for certain carriages. 
This new AD also adds an option, for certain replacements, of doing an 
inspection, and related investigative and corrective actions if 
necessary. This AD was prompted by a report of failure of both flap 
carriages. We are issuing this AD to detect and correct cracked, 
corroded, or fractured carriage spindles, which could lead to severe 
flap asymmetry, and could result in reduced control or loss of 
controllability of the airplane.

DATES: This AD is effective April 22, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 22, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
31, 2010 (75 FR 43803, July 27, 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; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 by searching for and locating Docket No. FAA-2014-
05-12 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 Docket 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 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-
6440; fax: (425) 917-6590; email: nancy.marsh@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2010-15-08, Amendment 39-16374 (75 FR 43803, 
July 27, 2010). AD 2010-15-08 applied to all The Boeing Company Model 
737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM 
published in the Federal Register on July 1, 2013 (78 FR 39193). The 
NPRM was prompted by a report of failure of both flap carriages. The 
NPRM proposed to continue to require repetitive inspections for 
discrepancies of each carriage spindle of the outboard mid-flaps; 
repetitive gap checks of the inboard and outboard carriages of the 
outboard mid-flaps to detect fractured carriage spindles; measuring to 
ensure that any new or serviceable carriage spindle meets minimum 
allowable diameter measurements taken at three locations; repetitive 
inspections, measurements, and overhaul of the carriage spindles; 
replacement of any carriage spindle when it has reached its maximum 
life limit; and corrective actions if necessary. The NPRM also proposed 
to require reducing the life limit of the carriages, reducing the 
repetitive interval for certain inspections and gap checks for certain 
carriages. The NPRM also proposed to add an option, for certain 
replacements, of doing an inspection, and related investigative and 
corrective actions if necessary. We are issuing this AD to detect and 
correct cracked, corroded, or fractured carriage spindles, which could 
lead to severe flap asymmetry, and could result in reduced control or 
loss of controllability of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 39193, July 1, 2013) and the FAA's response to each comment.

Request to Revise Note

    Boeing requested we revise note 1 to paragraph (m) of the NPRM (78 
FR 39193, July 1, 2013) to read, ``. . . Boeing (737) Standard Overhaul 
Practices Manual (SOPM), Revision 25 or later.'' Boeing stated that as 
its production standard changes, the SOPM is revised each time the SOPM 
is updated. Boeing stated that a global alternative method of 
compliance (AMOC) is required each time the SOPM is revised and this 
generates AMOC activity that does not enhance fleet safety.

[[Page 14978]]

    We disagree to revise Note 1 to paragraph (m) of this final rule 
because the text in Note 1 is informational guidance and does not 
relieve the requirement in paragraph (m) to obtain approval for the 
method used to apply plating, regardless of what revision of the SOPM 
is specified. We have not changed this final rule in this regard.

Request to Revise Requirement for Plating

    Boeing requested the following requirement in paragraph (m)(3) of 
the NPRM (78 FR 39193, July 1, 2013) be removed, ``The carriage must 
not be plated using any high velocity oxygen fuel (HVOF) thermal spray 
process.'' Boeing stated AD 2011-04-10, Amendment 39-16609 (76 FR 9498, 
February 18, 2011), and AD 2012-13-07, Amendment 39-17109 (77 FR 39153, 
July 2, 2012), required diligent inspection of HVOF coated carriages. 
Boeing stated that inspections to date have only found minor corrosion, 
well in advance of a potential unsafe condition. Boeing stated 
requiring carriages to be converted to nickel [plating] does not 
enhance fleet safety.
    We disagree to remove the requested phrase. The restriction against 
future application of HVOF plating of the flap carriages was 
coordinated and agreed to by The Boeing Company prior to issuance of 
the NPRM (78 FR 39193, July 1, 2013). Service experience has shown that 
the HVOF coating has insufficient reliability, therefore the 
restriction is necessary. We have not changed this final rule in this 
regard.

Clarification Regarding the Installation of Winglets

    Aviation Partners Boeing (APB) stated the installation of winglets 
per Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se) does 
not affect the accomplishment of the manufacturer's service 
instructions.
    We agree with APB's statement that the installation of winglets as 
specified in STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se) does 
not affect accomplishment of the requirements of this AD, and for 
airplanes on which STC ST01219SE is installed, a ``change in product'' 
(AMOC) approval request is not necessary to comply with the 
requirements of section 39.17 of the Federal Aviation Regulations (14 
CFR 39.17). We have redesignated paragraph (c) of the NPRM (78 FR 
39193, July 1, 2013) as (c)(1) and added this provision in new 
paragraph (c)(2) of this final rule.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 39193, July 1, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 39193, July 1, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 652 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained      12 work-hours x $85            $0  $1,020 per            $665,040 per
 from existing AD 2010-15-08,       per hour = $1,020.                 inspection cycle.     inspection cycle.
 Amendment 39-16374 (75 FR 43803,
 July 27, 2010)].
Inspections and measurements       2 work-hours x $85             $0  $170 per inspection   $110,840 per
 [actions retained from existing    per hour = $170.                   and measurement       inspection and
 AD 2010-15-08, Amendment 39-                                          cycle.                measurement cycle.
 16374 (75 FR 43803, July 27,
 2010)].
Overhauls [actions retained from   16 work-hours x $85   \1\ $28,000  $29,360 per overhaul  $19,142,720 per
 existing AD 2010-15-08,            per hour = $1,360.                 cycle.                overhaul cycle.
 Amendment 39-16374 (75 FR 43803,
 July 27, 2010)].
Replacements [actions retained     16 work-hours x $85   \2\ $60,000  $61,360 per           $40,006,720 per
 from existing AD 2010-15-08,       per hour = $1,360.                 replacement cycle.    replacement cycle.
 Amendment 39-16374 (75 FR 43803,
 July 27, 2010)].
----------------------------------------------------------------------------------------------------------------
\1\ $7,000 per spindle; 4 spindles per airplane.
\2\ $15,000 per spindle; 4 spindles per airplane.

    The new requirements of this AD add no additional economic burden.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,

[[Page 14979]]

    (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) 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), and adding 
the following new AD:

2014-05-12 The Boeing Company: Amendment 39-17785; Docket No. FAA-
2013-0542; Directorate Identifier 2011-NM-162-AD.

(a) Effective Date

    This AD is effective April 22, 2014.

(b) Affected ADs

    This AD supersedes AD 2010-15-08, Amendment 39-16374 (75 FR 
43803, July 27, 2010).

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in 
any category.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01219SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 57: Wings.

(e) Unsafe Condition

    This AD was prompted by a report of failure of both flap 
carriages. We are issuing this AD to detect and correct cracked, 
corroded, or fractured carriage spindles, which could lead to severe 
flap asymmetry, and could result in reduced control or loss of 
controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Compliance Times for Paragraphs (h) and (j) of This AD

    This paragraph restates the requirements of paragraph (g) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information that shortens the compliance times for 
certain inspections. The tables in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003; and Boeing Service Bulletin 737-57A1277, Revision 
3, dated May 16, 2012; specify the compliance times for paragraphs 
(g) through (k) of this AD. For carriage spindles that have 
accumulated the number of flight cycles or years in service 
specified in the ``Threshold'' column of the tables in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1277, 
Revision 1, dated November 25, 2003, accomplish the gap check, 
nondestructive test (NDT) inspection, and general visual inspection 
specified in paragraphs (h) and (j) of this AD within the 
corresponding interval after December 4, 2003 (the effective date AD 
2003-24-08, Amendment 39-13337 (68 FR 67027, December 1, 2003)), as 
specified in the ``Interval'' column of the tables in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1277, 
Revision 1, dated November 25, 2003, except as specified in 
paragraph (g)(1) or (g)(2) of this AD. Repeat the gap check, NDT, 
and general visual inspections at the intervals specified in the 
``Interval'' column of the tables in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003, except as specified in paragraph (g)(1) and 
(g)(2) of this AD. As of the effective date of this AD, accomplish 
the gap check, NDT inspection, and general visual inspections 
specified in paragraphs (h) and (j) of this AD within the 
corresponding interval as specified in the ``Interval'' column of 
the tables in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003, 
and thereafter at the intervals specified in Boeing Service Bulletin 
737-57A1277, Revision 3, dated May 16, 2012, except as specified in 
paragraphs (g)(1) and (g)(2) of this AD. Repeat the gap check, NDT, 
and general visual inspections thereafter at the intervals specified 
in the ``Interval'' column of the tables in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-57A1277, Revision 3, 
dated May 16, 2012, except as specified in paragraphs (g)(1) and 
(g)(2) of this AD.
    (1) The gap check does not have to be done at the same time as 
an NDT inspection; after doing an NDT inspection, the interval for 
doing the next gap check may be measured from the NDT inspection.
    (2) As carriage spindles gain flight cycles or years in service 
and move from one category in the ``Threshold'' column to another, 
they are subject to the repetitive inspection intervals 
corresponding to the new threshold category.

(h) Retained Work Package 2: Gap Check

    This paragraph restates the requirements of paragraph (h) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information. Perform a gap check of the inboard and 
outboard carriage of the left and right outboard mid-flaps to 
determine if there is a positive indication of a severed carriage 
spindle, in accordance with Work Package 2 of paragraph 3.B., ``Work 
Instructions,'' of Boeing Alert Service Bulletin 737-57A1277, 
Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737-
57A1277, Revision 3, dated May 16, 2012. As of the effective date of 
this AD, only Boeing Service Bulletin 737-57A1277, Revision 3, dated 
May 16, 2012, may be used to perform the actions specified in this 
paragraph.

(i) Retained Work Package 2: Corrective Actions with New Optional 
Actions and Exception

    This paragraph restates the requirements of paragraph (i) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information and new optional actions and exception. 
If there is a positive indication of a severed carriage spindle 
during the gap check required by paragraph (h) of this AD, before 
further flight, do the actions specified in paragraph (i)(1) or 
(i)(2) of this AD, except for carriage spindles on which an 
ultrasonic inspection has been done in accordance with the ``Work 
Instructions'' of Boeing Service Bulletin 737-57A1277, Revision 3, 
dated May 16, 2012; and the spindle has been confirmed not to be 
severed, no further actions are required by this paragraph for that 
carriage spindle.
    (1) Remove the carriage spindle and install a new or serviceable 
carriage spindle, in accordance with the ``Work Instructions'' of 
any service bulletin specified in paragraph (i)(1)(i), (i)(1)(ii), 
(i)(1)(iii), or (i)(1)(iv) of this AD. As of the effective date of 
this AD, only Boeing Service Bulletin 737-57A1277, Revision 3, dated 
May 16, 2012, may be used to perform the actions specified in this 
paragraph.
    (i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003.
    (ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May 
16, 2012.
    (iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5, 
dated February 9, 2009.
    (iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6, 
dated June 9, 2011.
    (2) Do a detailed inspection of the spindle to determine if 
there is corrosion, cracking, or a severed spindle, and, before 
further flight, do all related investigative and corrective actions, 
in accordance with the ``Work Instructions'' of Boeing Alert Service 
Bulletin 737-57A1277, Revision 1, dated November 25, 2003; or Boeing 
Service

[[Page 14980]]

Bulletin 737-57A1277, Revision 3, dated May 16, 2012. If, during the 
detailed inspection described in paragraph 4.b. of Work Package 2 of 
Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003; or Boeing Alert Service Bulletin 737-57A1277, 
Revision 3, dated May 16, 2012; a carriage spindle is found not to 
be severed, and no corrosion and no cracking is present, it can be 
reinstalled on the outboard mid-flap, in accordance with any service 
bulletin specified in paragraph (i)(2)(i), (i)(2)(ii), (i)(2)(iii), 
or (i)(2)(iv) of this AD. As of the effective date of this AD, only 
Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16, 2012, 
may be used to perform the actions specified in this paragraph.
    (i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003.
    (ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May 
16, 2012.
    (iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5, 
dated February 9, 2009.
    (iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6, 
dated June 9, 2011.

(j) Retained Work Package 1: NDT (Ultrasonic) and General Visual 
Inspections

    This paragraph restates the requirements of paragraph (j) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information. Perform an NDT (ultrasonic) inspection 
and general visual inspection for each carriage spindle of the left 
and right outboard mid-flaps to detect cracks, corrosion, or severed 
carriage spindles, in accordance with ``Work Package 1'' of the 
``Work Instructions'' of Boeing Alert Service Bulletin 737-57A1277, 
Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737-
57A1277, Revision 3, dated May 16, 2012. As of the effective date of 
this AD, only Boeing Service Bulletin 737-57A1277, Revision 3, dated 
May 16, 2012, may be used to perform the actions specified in this 
paragraph.

(k) Retained Work Package 1: Corrective Actions and New Optional Action

    This paragraph restates the requirements of paragraph (k) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information and new optional action. If any 
corroded, cracked, or severed carriage spindle is found during any 
inspection required by paragraph (j) of this AD: Before further 
flight, do the actions specified in paragraph (k)(1) or (k)(2) of 
this AD.
    (1) Remove the carriage spindle and install a new or serviceable 
carriage spindle, in accordance with any service bulletin identified 
in paragraph (k)(1)(i), (k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of 
this AD. As of the effective date of this AD, only Boeing Service 
Bulletin 737-57A1277, Revision 3, dated May 16, 2012, may be used to 
perform the actions specified in this paragraph.
    (i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003.
    (ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May 
16, 2012.
    (iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5, 
dated February 9, 2009.
    (iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6, 
dated June 9, 2011.
    (2) Do a detailed inspection of the spindle to determine if 
there is corrosion, cracking, or a severed spindle, in accordance 
with the ``Work Instructions'' of Boeing Alert Service Bulletin 737-
57A1277, Revision 1, dated November 25, 2003; or Boeing Service 
Bulletin 737-57A1277, Revision 3, dated May 16, 2012. If any 
corrosion, cracking, or a severed spindle is found, before further 
flight, install a new or serviceable carriage spindle, in accordance 
with any service bulletin identified in paragraph (k)(1)(i), 
(k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of this AD. As of the 
effective date of this AD, only Boeing Service Bulletin 737-57A1277, 
Revision 3, dated May 16, 2012, may be used to perform the actions 
specified in this paragraph.

(l) Retained Parts Installation Limitation

    This paragraph restates the requirements of paragraph (l) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010). Except 
as provided by paragraph (i) of this AD: As of December 4, 2003 (the 
effective date AD 2003-24-08, Amendment 39-13337 (68 FR 67027, 
December 1, 2003)), no person may install on any airplane a carriage 
spindle that has been removed as required by paragraph (i) or (k) of 
this AD, unless it has been overhauled in accordance with the ``Work 
Instructions'' of the applicable service bulletin identified in 
paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD. As of the 
effective date of this AD, only Boeing Service Bulletin 737-57A1277, 
Revision 3, dated May 16, 2012; or Boeing Alert Service Bulletin 
737-57A1218, Revision 6, dated June 9, 2011; may be used to perform 
the actions specified in this paragraph. To be eligible for 
installation under this paragraph, the carriage spindle must have 
been overhauled in accordance with the requirements of paragraph (m) 
of this AD.
    (1) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003.
    (2) Boeing Service Bulletin 737-57A1277, Revision 3, dated May 
16, 2012.
    (3) Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated 
February 9, 2009.
    (4) Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated 
June 9, 2011.

(m) Retained Electrodeposited Nickel Plating With New Plating 
Restrictions

    This paragraph restates the requirements of paragraph (m) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010) with 
revised plating application procedures. As of the effective date of 
this AD, during accomplishment of any overhaul specified in 
paragraph (l) or (o) of this AD, follow the requirements specified 
in paragraphs (m)(1), (m)(2), and (m)(3) of this AD during 
application of the plating to the carriage spindle, in accordance 
with a method approved by the Manager, Seattle, Aircraft 
Certification Office (ACO), FAA. 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.
    (1) The maximum deposition rate of the nickel plating in any one 
plating/baking cycle must not exceed 0.002-inch-per-hour.
    (2) Begin the hydrogen embrittlement relief bake within 10 hours 
after application of the nickel plating, or less than 24 hours after 
the current was first applied to the part, whichever is first.
    (3) The carriage must not be plated using any high velocity 
oxygen fuel (HVOF) thermal spray process.

    Note 1 to paragraph (m) of this AD: Guidance on the application 
of nickel plating can be found in Chapter 20-42-09, Electrodeposited 
Nickel Plating, of the Boeing (737) Standard Overhaul Practices 
Manual, Revision 25, dated July 1, 2009.

(n) Retained Exception to Reporting Recommendations

    This paragraph restates the provisions of paragraph (n) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information. Although Boeing Alert Service Bulletin 
737-57A1277, Revision 1, dated November 25, 2003; and Boeing Service 
Bulletin 737-57A1277, Revision 3, dated May 16, 2012; recommend that 
operators report inspection findings to the manufacturer, this AD 
does not require reporting.

(o) Retained Inspections, Measurements, and Overhauls of the Carriage 
Spindle With Clarification of Overhaul Restrictions

    This paragraph restates the requirements of paragraph (o) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010) with 
clarification of overhaul restrictions. At the applicable times 
specified in paragraphs (o)(1) and (o)(2) of this AD: Do the 
detailed inspection for corrosion, pitting, and cracking of the 
carriage spindle; magnetic particle inspection for cracking of the 
carriage spindle; measurements of the spindle to determine if it 
meets the allowable minimum diameter; overhauls of the carriage 
spindle; and applicable corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1218, Revision 5, dated February 9, 2009; or Boeing Alert Service 
Bulletin 737-57A1218, Revision 6, dated June 9, 2011. As of the 
effective date of this AD, only Boeing Alert Service Bulletin 737-
57A1218, Revision 6, dated June 9, 2011, may be used to perform the 
actions specified in this paragraph. The applicable corrective 
actions must be done before further flight. Repeat these actions 
thereafter at intervals not to exceed every 12,000 flight cycles on 
the carriage spindle or every 8 years since first installation of 
the carriage spindle on the airplane, whichever comes first. As of 
the effective date of this AD: For any overhaul required by this 
paragraph, the carriage spindle must be overhauled in accordance 
with the requirements of paragraph (m) of this AD.
    (1) For Model 737-100, -200, -200C series airplanes: At the 
later of the times specified in paragraphs (o)(1)(i) and (o)(1)(ii) 
of this AD.
    (i) Before the accumulation of 12,000 total flight cycles on the 
carriage spindle since new or overhauled, or within 8 years after 
the installation of the new or overhauled part, whichever comes 
first.
    (ii) Within 1 year after August 31, 2010 (the effective date of 
AD 2010-15-08,

[[Page 14981]]

Amendment 39-16374 (75 FR 43803, July 27, 2010)).
    (2) For Model -300, -400, and -500 series airplanes: At the 
later of the times specified in paragraphs (o)(2)(i) and (o)(2)(ii) 
of this AD.
    (i) Before the accumulation of 12,000 total flight cycles on the 
carriage spindle since new or overhauled, or within 8 years after 
the installation of the new or overhauled part, whichever comes 
first.
    (ii) Within 2 years after August 31, 2010 (the effective date of 
AD 2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010)).

(p) Retained Carriage Spindle Replacement for Model 737-100, -200, and 
-200C Series Airplanes

    This paragraph restates the requirements of paragraph (p) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information and a shortened compliance time. For 
Model 737-100, -200, -200C series airplanes: Replace the carriage 
spindle with a new or documented (for which the service life, in 
total flight cycles, is known) carriage spindle, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-57A1218, Revision 5, dated February 9, 2009; or Boeing Alert 
Service Bulletin 737-57A1218, Revision 6, dated June 9, 2011; at the 
earlier of the times specified in paragraphs (p)(1) and (p)(2) of 
this AD, except as required by paragraph (r) of this AD. As of the 
effective date of this AD, only Boeing Alert Service Bulletin 737-
57A1218, Revision 6, dated June 9, 2011, may be used to perform the 
replacement. Overhauling the carriage spindles does not zero-out the 
flight cycles. Total flight cycles accumulate since new.
    (1) At the later of the times specified in paragraphs (p)(1)(i) 
and (p)(1)(ii) of this AD.
    (i) Before the accumulation of 48,000 total flight cycles on the 
new or overhauled carriage.
    (ii) Within 3 years or 7,500 flight cycles after August 31, 2010 
(the effective date of AD 2010-15-08, Amendment 39-16374 (75 FR 
43803, July 27, 2010)), whichever occurs first.
    (2) Before the accumulation of 40,000 total flight cycles on the 
new or overhauled carriage or 6 months after the effective date of 
this AD, whichever occurs later.

(q) Retained Carriage Spindle Replacement for Model 737-300, -400, and 
-500 Series Airplanes

    This paragraph restates the requirements of paragraph (q) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised service information and a shortened compliance time. For 
Model 737-300, -400, and -500 series airplanes: Replace the carriage 
spindle with a new or documented (for which the service life, in 
flight cycles, is known) carriage spindle, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1218, Revision 5, dated February 9, 2009; or Boeing Alert Service 
Bulletin 737-57A1218, Revision 6, dated June 9, 2011; at the later 
of the times specified in paragraphs (q)(1) and (q)(2) of this AD, 
except as required by paragraph (r) of this AD. As of the effective 
date of this AD, only Boeing Alert Service Bulletin 737-57A1218, 
Revision 6, dated June 9, 2011, may be used to perform the 
replacement required by this paragraph. Overhauling the carriage 
spindles does not zero-out the flight cycles. Total flight cycles 
accumulate since new.
    (1) Before the accumulation of 40,000 total flight cycles on the 
new or overhauled carriage.
    (2) Within 6 years or 15,000 flight cycles after August 31, 2010 
(the effective date of AD 2010-15-08, Amendment 39-16374 (75 FR 
43803, July 27, 2010)), whichever occurs first.

(r) Retained Carriage Spindle Replacement for Airplanes With an 
Undocumented Carriage

    This paragraph restates the requirements of paragraph (r) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010). For 
airplanes with an undocumented carriage: Do the applicable actions 
specified in paragraph (p) or (q) of this AD at the applicable time 
specified in paragraph (r)(1) or (r)(2) of this AD.
    (1) For Model 737-100, -200, -200C series airplanes: Do the 
actions specified in paragraph (p) of this AD at the time specified 
in paragraph (p)(1)(ii) of this AD.
    (2) For Model -300, -400, and -500 series airplanes: Do the 
actions specified in paragraph (q) of this AD at the time specified 
in paragraph (q)(2) of this AD.

(s) Retained Repetitive Replacements of Carriage Spindle

    This paragraph restates the requirements of paragraph (s) of AD 
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with 
revised compliance times.
    (1) For airplanes on which the actions required by paragraph (p) 
or (q) of this AD, as applicable, have been done as of the effective 
date of this AD: Repeat the replacement of the carriage spindle 
specified by paragraph (p) or (q) of this AD, as applicable, one 
time at the later of the times specified in paragraphs (s)(1)(i) and 
(s)(1)(ii) of this AD, and thereafter at intervals not to exceed 
40,000 total flight cycles on the new or overhauled carriage 
spindle.
    (i) Before the accumulation of 40,000 total flight cycles on the 
new or overhauled carriage.
    (ii) Within 6 years or 15,000 flight cycles after August 31, 
2010 (the effective date of AD 2010-15-08, Amendment 39-16374 (75 FR 
43803, July 27, 2010)), whichever occurs first.
    (2) For airplanes on which the actions required by paragraph (p) 
or (q) of this AD, as applicable, have not been done as of the 
effective date of this AD: Repeat the replacement of the carriage 
spindle specified by paragraph (p) or (q) of this AD, as applicable, 
thereafter at intervals not to exceed 40,000 total flight cycles on 
the new or overhauled carriage spindle.

(t) Exception to Compliance Time

    Where Boeing Service Bulletin 737-57A1277, Revision 3, dated May 
16, 2012, and Boeing Alert Service Bulletin 737-57A1218, Revision 6, 
dated June 9, 2011, specify a compliance time after the dates of 
those service bulletins, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

(u) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) through (s) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Alert 
Service Bulletin 737-57A1277, Revision 2, dated June 9, 2011, which 
is not incorporated by reference in this AD.

(v) Alternative Methods of Compliance (AMOCs)

    (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. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (w) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, 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.
    (4) AMOCs previously approved in accordance with AD 2003-24-08, 
Amendment 39-13377 (68 FR 67027, December 1, 2003), or AD 2010-15-
08, Amendment 39-16374 (75 FR 43803, July 27, 2010), are approved as 
AMOCs for individual repairs are acceptable for compliance with the 
corresponding provisions of this AD. All other existing AMOCs are 
not acceptable.

(w) Related Information

    (1) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: (425) 917-6440; fax: (425) 917-6590; email: 
nancy.marsh@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (x)(5) and (x)(6) of this AD.

(x) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.

[[Page 14982]]

    (3) The following service information was approved for IBR on 
April 22, 2014.
    (i) Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated 
June 9, 2011.
    (ii) Boeing Alert Service Bulletin 737-57A1277, Revision 3, 
dated May 16, 2012.
    (4) The following service information was approved for IBR on 
August 31, 2010 (75 FR 43803, July 27, 2010).
    (i) Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated 
February 9, 2009.
    (ii) Boeing Alert Service Bulletin 737-57A1277, Revision 1, 
dated November 25, 2003.
    (5) For Boeing 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; 
Internet https://www.myboeingfleet.com.
    (6) You may view this service information at 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.
    (7) You may view this 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 18, 2014.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04819 Filed 3-17-14; 8:45 am]
BILLING CODE 4910-13-P