Airworthiness Directives; The Boeing Company Airplanes, 36672-36675 [2014-15251]

Download as PDF 36672 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0346; Directorate Identifier 2014–NM–010–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This proposed AD was prompted by reports of cracks in fuselage frames, and a report of a missing strap that was not installed on a fuselage frame during production. This proposed AD would require an inspection to determine if the strap adjacent to a certain stringer is installed, and repair if missing; repetitive inspections of the frame for cracking or a severed frame web; and related investigative and corrective actions if necessary. This proposed AD also provides optional actions to terminate certain repetitive inspections. We are proposing this AD to detect and correct missing fuselage frame straps and frame cracking that can result in severed frames. Continued operation of the airplane with multiple adjacent severed frames, or the combination of a severed frame and fuselage skin chemical mill cracks, can result in uncontrolled decompression of the airplane. DATES: We must receive comments on this proposed AD by August 14, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, emcdonald on DSK67QTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:59 Jun 27, 2014 Jkt 232001 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–2014– 0346; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6450; fax: 425–917–6590; email: alan.pohl@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2014–0346; Directorate Identifier 2014– NM–010–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of fuselage frame cracking, and a report of a missing strap that was not installed on a fuselage frame during production. One report was a crack in the frame at station 328 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 and a crack that severed the frame at station 360 on the right side of an airplane that had 59,756 total flight cycles. The frame web and the failsafe chord were completely severed. We have received ten reports of cracks in the frames at station 328 between stringers S–20R and S–21R on Model 737–200, 737–300, and 737–500 series airplanes that had accumulated between 43,581 and 73,655 total flight cycles. These cracks were in the frame web at an open tool hole, in the frame web at the end fastener in the inner chord, and in the frame web notch. The cracks were from 0.3 inch to 3.0 inches long. We have also received 14 reports of cracks in the frames at station 360 between stringers S–19R and S–21R on Model 737–200 and 737–300 series airplanes that had accumulated between 42,183 and 66,588 total flight cycles. These cracks were in the frame web at an open tool hole, in the frame web at an insulation blanket stud hole, in the frame web at an end fastener in the doubler, and in the inner flange at the end fastener in the doubler. The cracks were from 2.5 inches long to cracks that severed the frame web and fail-safe chord. We have received a report of three cracks in the frame at station 380 between stringers S–18R and S–20R on a Model 737–300 series airplane with 32,218 total flight cycles. Cracks were in the frame inner flange at fasteners common to the bulkhead support angle. One of the three cracks was also in the doubler. We have received a report of a strap that was not installed on the frame at station 312 adjacent to stringer S–22R on a Model 737–400 series airplane with 24,037 total flight cycles. Investigation of the drawings determined that this was an incorrect frame configuration and that the strap should have been installed. Missing fuselage frame straps and frame cracking can result in severed frames. Continued operation of the airplane with multiple adjacent severed frames, or the combination of a severed frame and fuselage skin chemical mill cracks, can result in uncontrolled decompression of the airplane. Relevant Service Information We reviewed Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA 2014– 0346. E:\FR\FM\30JNP1.SGM 30JNP1 36673 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require an inspection to determine if the strap adjacent to a certain stringer is installed, and repair if missing; repetitive inspections of the frame for cracking or a severed frame web; and related investigative and corrective actions if necessary. This proposed AD also provides optional actions to terminate the repetitive inspections. The phrase ‘‘related investigative actions’’ is used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Tables 13 through 15 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, specify postmodification inspections at certain locations, which may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 129.109(b)(2)). However, this NPRM does not propose to require those post-modification inspections. This difference has been coordinated with Boeing. Costs of Compliance We estimate that this proposed AD affects 417 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspections .................... 21 work-hours × $85 per hour = $1,785 per inspection cycle. $0 Cost per product Parts cost We have received no definitive data that would enable us to provide cost estimates for certain on-condition actions specified in this proposed AD. Cost on U.S. operators $1,785 per inspection cycle. However, we estimate the following costs to do any necessary repairs of the station 328 frame and the station 360 frame. We have no way of determining $744,345 per inspection cycle. the number of aircraft that might need these repairs: ON-CONDITION COSTS Action Labor cost Parts cost Frame 328 repair ............................... Frame 360 repair ............................... 25 work-hours × $85 per hour = $2,125 ...................................................... 5 work-hours × $85 per hour = $425 ........................................................... Negligible ... Negligible ... Authority for This Rulemaking emcdonald on DSK67QTVN1PROD with PROPOSALS Cost per product 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 proposed regulation is within the scope of that VerDate Mar<15>2010 17:59 Jun 27, 2014 Jkt 232001 authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 $2,125 425 (2) Is not a ‘‘significant rule’’ under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, E:\FR\FM\30JNP1.SGM 30JNP1 36674 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2014–0346; Directorate Identifier 2014– NM–010–AD. (a) Comments Due Date We must receive comments by August 14, 2014. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracks in fuselage frames, and a report of a missing strap that was not installed on a fuselage frame during production. We are issuing this AD to detect and correct missing fuselage frame straps and frame cracking that can result in severed frames. Continued operation of the airplane with multiple adjacent severed frames, or the combination of a severed frame and fuselage skin chemical mill cracks, can result in uncontrolled decompression of the airplane. emcdonald on DSK67QTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Group 1 Airplane Actions For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do the repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (h) Groups 2 Through 7 Airplanes: Inspection for Strap Installation at Station 312 For airplanes identified as Groups 2 through 7 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in Tables 2 and VerDate Mar<15>2010 17:59 Jun 27, 2014 Jkt 232001 3 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do a general visual inspection of the frame at station 312 to determine if the strap adjacent to stringer S–22R is installed, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. If the strap is not installed, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (i) Groups 2 Through 6 Airplanes With Less Than 28,300 Total Flight Cycles: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Stations 328, 344, and 360 For airplanes identified as Groups 2 through 6 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, that have accumulated less than 28,300 total flight cycles as of the effective date of this AD: Do the actions required by paragraphs (i)(1) and (i)(2) of this AD. (1) At the applicable times specified in Tables 4, 5, 7, and 8 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD: Do detailed and eddy current inspections of the frame at stations 328, 344, and 360 for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable time and intervals specified in Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, until the inspection required by paragraph (i)(2) of this AD is done. Doing the preventative modification of the frame at station 360 and the repair of the frame at station 328, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD, terminates the applicable repetitive inspection requirements of paragraph (i)(1) of this AD. (2) At the applicable time specified in Tables 4, 5, 7, and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, do the actions specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. Accomplishing the initial inspections required by paragraph (i)(2) of this AD terminates the inspections required by paragraph (i)(1) of this AD. Doing the preventative modification of the frame at station 360 and the repair of the frame at station 328, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD, terminates the applicable repetitive inspection requirements of paragraph (i)(2)(i) and (i)(2)(ii) of this AD. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 (i) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360 for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. (ii) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360 for cracking or a severed frame web; and external detailed and eddy current inspections of the fuselage skin for cracking; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable time and intervals specified in Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. (j) Groups 2 Through 6 Airplanes With 28,300 Total Flight Cycles or More: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Stations 328, 344, and 360 For airplanes identified as Groups 2 through 6 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, that have accumulated 28,300 total flight cycles or more as of the effective date of this AD: At the applicable times specified in Tables 4, 5, 7, and 8 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do the inspections specified in paragraphs (j)(1) or (j)(2) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections specified in paragraphs (j)(1) or (j)(2) of this AD thereafter at the applicable time and intervals specified in Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Doing the preventative modification of the frame at station 360 and the repair of the frame at station 328, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD, terminates the applicable repetitive inspection requirements of this paragraph. (1) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360 for cracking or a severed frame web. E:\FR\FM\30JNP1.SGM 30JNP1 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules (2) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360 for cracking or a severed frame web; and external detailed and eddy current inspections of the fuselage skin for cracking. (k) Group 7 Airplanes: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Station 328 For airplanes identified as Group 7 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in Table 6 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do a detailed inspection of the frame at station 328 for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Doing the repair of the frame at station 328, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD, terminates the repetitive inspection requirements of this paragraph. emcdonald on DSK67QTVN1PROD with PROPOSALS (l) Groups 2 Through 5 Airplanes: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Station 380 For airplanes identified as Groups 2 through 5 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in Tables 9 and 10 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do detailed and eddy current inspections of the frame at station 380 for cracking or a severed frame web; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. (m) Exceptions to Service Information (1) Where Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, specifies a compliance time after the ‘‘original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, specifies to contact Boeing VerDate Mar<15>2010 17:59 Jun 27, 2014 Jkt 232001 for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (n) Post-Repair Inspections and PostModification Inspections The post-repair and post-modification inspections specified in Tables 13 through 15 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, are not required by this AD. Note 1 to paragraph (n) of this AD: The post-repair and post-modification inspections specified in Tables 13 through 15 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, are not required by this AD. (o) 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 (p)(1) 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 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. (p) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6450; fax: 425–917–6590; email: alan.pohl@faa.gov. (2) 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 36675 information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on June 19, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–15251 Filed 6–27–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0345; Directorate Identifier 2013–NM–230–AD] RIN 2120–AA64 Airworthiness Directives; Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 400T, and MU–300 airplanes. This proposed AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). This proposed AD would require an inspection to determine if PTAs having a certain serial number and part number are installed, and replacement if they are installed. This proposed AD would also require repetitive replacements of PTAs with new PTAs or certain overhauled PTAs. We are proposing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by August 29, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room SUMMARY: E:\FR\FM\30JNP1.SGM 30JNP1

Agencies

[Federal Register Volume 79, Number 125 (Monday, June 30, 2014)]
[Proposed Rules]
[Pages 36672-36675]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-15251]



[[Page 36672]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0346; Directorate Identifier 2014-NM-010-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and 
-500 series airplanes. This proposed AD was prompted by reports of 
cracks in fuselage frames, and a report of a missing strap that was not 
installed on a fuselage frame during production. This proposed AD would 
require an inspection to determine if the strap adjacent to a certain 
stringer is installed, and repair if missing; repetitive inspections of 
the frame for cracking or a severed frame web; and related 
investigative and corrective actions if necessary. This proposed AD 
also provides optional actions to terminate certain repetitive 
inspections. We are proposing this AD to detect and correct missing 
fuselage frame straps and frame cracking that can result in severed 
frames. Continued operation of the airplane with multiple adjacent 
severed frames, or the combination of a severed frame and fuselage skin 
chemical mill cracks, can result in uncontrolled decompression of the 
airplane.

DATES: We must receive comments on this proposed AD by August 14, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, 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-2014-
0346; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 
425-917-6590; email: alan.pohl@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2014-0346; 
Directorate Identifier 2014-NM-010-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of fuselage frame cracking, and a report 
of a missing strap that was not installed on a fuselage frame during 
production. One report was a crack in the frame at station 328 and a 
crack that severed the frame at station 360 on the right side of an 
airplane that had 59,756 total flight cycles. The frame web and the 
failsafe chord were completely severed.
    We have received ten reports of cracks in the frames at station 328 
between stringers S-20R and S-21R on Model 737-200, 737-300, and 737-
500 series airplanes that had accumulated between 43,581 and 73,655 
total flight cycles. These cracks were in the frame web at an open tool 
hole, in the frame web at the end fastener in the inner chord, and in 
the frame web notch. The cracks were from 0.3 inch to 3.0 inches long.
    We have also received 14 reports of cracks in the frames at station 
360 between stringers S-19R and S-21R on Model 737-200 and 737-300 
series airplanes that had accumulated between 42,183 and 66,588 total 
flight cycles. These cracks were in the frame web at an open tool hole, 
in the frame web at an insulation blanket stud hole, in the frame web 
at an end fastener in the doubler, and in the inner flange at the end 
fastener in the doubler. The cracks were from 2.5 inches long to cracks 
that severed the frame web and fail-safe chord.
    We have received a report of three cracks in the frame at station 
380 between stringers S-18R and S-20R on a Model 737-300 series 
airplane with 32,218 total flight cycles. Cracks were in the frame 
inner flange at fasteners common to the bulkhead support angle. One of 
the three cracks was also in the doubler.
    We have received a report of a strap that was not installed on the 
frame at station 312 adjacent to stringer S-22R on a Model 737-400 
series airplane with 24,037 total flight cycles. Investigation of the 
drawings determined that this was an incorrect frame configuration and 
that the strap should have been installed.
    Missing fuselage frame straps and frame cracking can result in 
severed frames. Continued operation of the airplane with multiple 
adjacent severed frames, or the combination of a severed frame and 
fuselage skin chemical mill cracks, can result in uncontrolled 
decompression of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for and locating Docket No. FAA 2014-0346.

[[Page 36673]]

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require an inspection to determine if the 
strap adjacent to a certain stringer is installed, and repair if 
missing; repetitive inspections of the frame for cracking or a severed 
frame web; and related investigative and corrective actions if 
necessary. This proposed AD also provides optional actions to terminate 
the repetitive inspections.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, and (2) further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 737-53A1323, dated December 6, 2013, 
specifies to contact the manufacturer for instructions on how to repair 
certain conditions, but this proposed AD would require repairing those 
conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.
    Tables 13 through 15 in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1323, dated December 6, 2013, specify 
post-modification inspections at certain locations, which may be used 
in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) 
of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 
129.109(b)(2)). However, this NPRM does not propose to require those 
post-modification inspections. This difference has been coordinated 
with Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 417 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Inspections....................  21 work-hours x $85 per              $0   $1,785 per          $744,345 per
                                  hour = $1,785 per                         inspection cycle.   inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for certain on-condition actions specified in this 
proposed AD. However, we estimate the following costs to do any 
necessary repairs of the station 328 frame and the station 360 frame. 
We have no way of determining the number of aircraft that might need 
these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                Action                            Labor cost                   Parts cost             product
----------------------------------------------------------------------------------------------------------------
Frame 328 repair......................  25 work-hours x $85 per hour =  Negligible..............          $2,125
                                         $2,125.
Frame 360 repair......................  5 work-hours x $85 per hour =   Negligible..............             425
                                         $425.
----------------------------------------------------------------------------------------------------------------

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 proposed 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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 36674]]

the FAA proposes to amend 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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2014-0346; Directorate Identifier 
2014-NM-010-AD.

(a) Comments Due Date

    We must receive comments by August 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 737-
53A1323, dated December 6, 2013.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracks in fuselage frames, 
and a report of a missing strap that was not installed on a fuselage 
frame during production. We are issuing this AD to detect and 
correct missing fuselage frame straps and frame cracking that can 
result in severed frames. Continued operation of the airplane with 
multiple adjacent severed frames, or the combination of a severed 
frame and fuselage skin chemical mill cracks, can result in 
uncontrolled decompression of the airplane.

(f) Compliance

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

(g) Group 1 Airplane Actions

    For airplanes identified as Group 1 in Boeing Alert Service 
Bulletin 737-53A1323, dated December 6, 2013: At the applicable time 
specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1323, dated December 6, 2013, except 
as provided by paragraph (m)(1) of this AD, do the repair using a 
method approved in accordance with the procedures specified in 
paragraph (o) of this AD.

(h) Groups 2 Through 7 Airplanes: Inspection for Strap Installation at 
Station 312

    For airplanes identified as Groups 2 through 7 in Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013: At the 
applicable time specified in Tables 2 and 3 of Paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, except as provided by paragraph (m)(1) of this AD, 
do a general visual inspection of the frame at station 312 to 
determine if the strap adjacent to stringer S-22R is installed, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013. If the strap 
is not installed, before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(o) of this AD.

(i) Groups 2 Through 6 Airplanes With Less Than 28,300 Total Flight 
Cycles: Repetitive Inspections, Related Investigative Actions, and 
Corrective Actions at Stations 328, 344, and 360

    For airplanes identified as Groups 2 through 6 in Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013, that have 
accumulated less than 28,300 total flight cycles as of the effective 
date of this AD: Do the actions required by paragraphs (i)(1) and 
(i)(2) of this AD.
    (1) At the applicable times specified in Tables 4, 5, 7, and 8 
of Paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1323, dated December 6, 2013, except as provided by paragraph 
(m)(1) of this AD: Do detailed and eddy current inspections of the 
frame at stations 328, 344, and 360 for cracking or a severed frame 
web; and do all applicable related investigative and corrective 
actions; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1323, dated December 6, 2013, 
except as specified in paragraph (m)(2) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Repeat the applicable inspections thereafter at the 
applicable time and intervals specified in Paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, until the inspection required by paragraph (i)(2) 
of this AD is done. Doing the preventative modification of the frame 
at station 360 and the repair of the frame at station 328, as 
applicable, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1323, dated December 6, 2013, 
except as specified in paragraph (m)(2) of this AD, terminates the 
applicable repetitive inspection requirements of paragraph (i)(1) of 
this AD.
    (2) At the applicable time specified in Tables 4, 5, 7, and 8 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1323, dated December 6, 2013, do the actions specified in 
paragraph (i)(2)(i) or (i)(2)(ii) of this AD. Accomplishing the 
initial inspections required by paragraph (i)(2) of this AD 
terminates the inspections required by paragraph (i)(1) of this AD. 
Doing the preventative modification of the frame at station 360 and 
the repair of the frame at station 328, as applicable, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-53A1323, dated December 6, 2013, except as specified in 
paragraph (m)(2) of this AD, terminates the applicable repetitive 
inspection requirements of paragraph (i)(2)(i) and (i)(2)(ii) of 
this AD.
    (i) Do detailed and eddy current inspections of the frame at 
stations 328, 344, and 360 for cracking or a severed frame web; and 
do all applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013, except as 
specified in paragraph (m)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections specified in this paragraph thereafter at the 
applicable time and intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013.
    (ii) Do detailed and eddy current inspections of the frame at 
stations 328, 344, and 360 for cracking or a severed frame web; and 
external detailed and eddy current inspections of the fuselage skin 
for cracking; and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, except as specified in paragraph (m)(2) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight. Repeat the applicable inspections thereafter 
at the applicable time and intervals specified in Paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013.

(j) Groups 2 Through 6 Airplanes With 28,300 Total Flight Cycles or 
More: Repetitive Inspections, Related Investigative Actions, and 
Corrective Actions at Stations 328, 344, and 360

    For airplanes identified as Groups 2 through 6 in Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013, that have 
accumulated 28,300 total flight cycles or more as of the effective 
date of this AD: At the applicable times specified in Tables 4, 5, 
7, and 8 of Paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1323, dated December 6, 2013, except as provided by 
paragraph (m)(1) of this AD, do the inspections specified in 
paragraphs (j)(1) or (j)(2) of this AD; and do all applicable 
related investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1323, dated December 6, 2013, except as specified in paragraph 
(m)(2) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the applicable 
inspections specified in paragraphs (j)(1) or (j)(2) of this AD 
thereafter at the applicable time and intervals specified in 
Paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1323, dated December 6, 2013. Doing the preventative 
modification of the frame at station 360 and the repair of the frame 
at station 328, as applicable, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, except as specified in paragraph (m)(2) of this 
AD, terminates the applicable repetitive inspection requirements of 
this paragraph.
    (1) Do detailed and eddy current inspections of the frame at 
stations 328, 344, and 360 for cracking or a severed frame web.

[[Page 36675]]

    (2) Do detailed and eddy current inspections of the frame at 
stations 328, 344, and 360 for cracking or a severed frame web; and 
external detailed and eddy current inspections of the fuselage skin 
for cracking.

(k) Group 7 Airplanes: Repetitive Inspections, Related Investigative 
Actions, and Corrective Actions at Station 328

    For airplanes identified as Group 7 in Boeing Alert Service 
Bulletin 737-53A1323, dated December 6, 2013: At the applicable time 
specified in Table 6 of Paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1323, dated December 6, 2013, except 
as provided by paragraph (m)(1) of this AD, do a detailed inspection 
of the frame at station 328 for cracking or a severed frame web; and 
do all applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013, except as 
specified in paragraph (m)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections specified in this paragraph thereafter at the 
applicable time and intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013. Doing the repair of the frame at station 328, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013, except as 
specified in paragraph (m)(2) of this AD, terminates the repetitive 
inspection requirements of this paragraph.

(l) Groups 2 Through 5 Airplanes: Repetitive Inspections, Related 
Investigative Actions, and Corrective Actions at Station 380

    For airplanes identified as Groups 2 through 5 in Boeing Alert 
Service Bulletin 737-53A1323, dated December 6, 2013: At the 
applicable time specified in Tables 9 and 10 of Paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, except as provided by paragraph (m)(1) of this AD, 
do detailed and eddy current inspections of the frame at station 380 
for cracking or a severed frame web; and do all applicable 
corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, except as specified in paragraph (m)(2) of this 
AD. Do all applicable corrective actions before further flight. 
Repeat the inspections specified in this paragraph thereafter at the 
applicable time and intervals specified in Paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013.

(m) Exceptions to Service Information

    (1) Where Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, specifies a compliance time after the ``original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) If any cracking is found during any inspection required by 
this AD, and Boeing Alert Service Bulletin 737-53A1323, dated 
December 6, 2013, specifies to contact Boeing for appropriate 
action: Before further flight, repair the cracking using a method 
approved in accordance with the procedures specified in paragraph 
(o) of this AD.

(n) Post-Repair Inspections and Post-Modification Inspections

    The post-repair and post-modification inspections specified in 
Tables 13 through 15 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1323, dated December 6, 2013, are not 
required by this AD.
    Note 1 to paragraph (n) of this AD: The post-repair and post-
modification inspections specified in Tables 13 through 15 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1323, dated December 6, 2013, may be used in support of 
compliance with section 121.1109(c)(2) or 129.109(b)(2) of the 
Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 
129.109(b)(2)). The corresponding actions specified in the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1323, dated December 6, 2013, are not required by this AD.

(o) 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 (p)(1) 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 
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.

(p) Related Information

    (1) For more information about this AD, contact Alan Pohl, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6450; fax: 425-917-6590; email: alan.pohl@faa.gov.
    (2) 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.

    Issued in Renton, Washington, on June 19, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-15251 Filed 6-27-14; 8:45 am]
BILLING CODE 4910-13-P