Airworthiness Directives; The Boeing Company Airplanes, 49903-49906 [2013-18090]

Download as PDF 49903 Rules and Regulations Federal Register Vol. 78, No. 159 Friday, August 16, 2013 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. MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0637; Directorate Identifier 2012–NM–006–AD; Amendment 39–17532; AD 2013–15–16] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. This AD was prompted by a report of an inboard main landing gear (MLG) door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. This AD requires repetitive inspections for cracking of the inboard MLG door hinge fittings; and replacement or modification of cracked fittings. This AD also provides an option to remove the affected MLG door. We are issuing this AD to detect and correct fatigue cracking in the inboard MLG door hinge fittings, which could result in loss of the MLG door assembly from the airplane, and the MLG door assembly could impact the flight control surfaces and result in reduced controllability of the airplane. SUMMARY: This AD is effective September 20, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 20, 2013. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, tkelley on DSK3SPTVN1PROD with RULES DATES: VerDate Mar<15>2010 17:24 Aug 15, 2013 Jkt 229001 You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 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 include an AD that would apply to the specified products. The NPRM published in the Federal Register on June 18, 2012 (77 FR 36222). The NPRM proposed to require repetitive inspections for cracking of the inboard MLG door hinge fittings; and modification of cracked fittings, which would terminate the repetitive inspections. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 36222, June 18, 2012) and the FAA’s response to each comment. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Request To Extend Compliance Time American Airlines requested that we revise the NPRM (77 FR 36222, June 18, 2012) to extend the compliance time for the initial inspections from 10,000 total flight cycles to before 18,000 total flight cycles. American Airlines stated that the FAA has not provided sufficient evidence to warrant issuance of regulatory action with such a reduced compliance time. American Airlines calculated that the event described in the service information represents only 0.085 percent of the airplanes under U.S. registry, and that the event described occurred at 24,000 total flight cycles. We disagree with the request to extend the compliance time. In developing an appropriate compliance time for this action, we considered the safety implications, parts availability, and normal maintenance schedules for the timely accomplishment of the inspections and modifications. There is additional data related to the MLG door hinge failures that is not included in the manufacturer’s service bulletin. Up to 10 percent of hinges inspected to date have been found with cracking. The cracking occurred between 11,000 and 24,000 total flight cycles, and has been found on both hinges of the inboard MLG door. In consideration of these items, we have determined that a compliance time of before 10,000 total flight cycles will ensure an acceptable level of safety and allow the inspections and modifications to be done during scheduled maintenance intervals for most affected operators. We have not changed the AD in this regard. Request To Allow New Hinges Having Part Numbers (P/Ns) 113A8341–1 and 113A8341–2 American Airlines requested that we revise paragraph (g) of the NPRM (77 FR 36222, June 18, 2012) to allow installation of new hinges having P/Ns 113A8341–1 and 113A8341–2 as replacements for cracked hinges found during the inspections. American Airlines stated that paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011 (referred to in the NPRM as the appropriate source of service information), implies that an operator may install a new set of hinges having P/Ns 113A8341–1 and 113A8341–2 and restart the inspection threshold and E:\FR\FM\16AUR1.SGM 16AUR1 49904 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations interval; however, the Accomplishment Instructions recommend installation of new hinges having P/Ns 113A8341–9 and 113A8341–10 if cracking is found. American Airlines stated that installation of a new set of hinges having P/Ns 113A8341–1 and 113A8341–2 should be acceptable as long as the on-going repetitive inspections are accomplished as defined in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 52A1167, dated December 1, 2011. We agree to allow replacement of cracked hinges with new hinges having P/Ns 113A8341–1 and 113A8341–2, as long as inspections of the replacement hinges are accomplished at the time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. We have added new paragraph (h)(2) to this AD to clarify that installing new MLG door hinge fittings having P/N 113A8341–1 and 113A8341–2, is acceptable for compliance with the modification specified in paragraphs (g)(1)(ii) and (g)(2)(i) of this AD. Paragraph (h)(2) also specifies that installation of the MLG door hinge fittings having P/N 113A8341–1 and 113A8341–2, must be done using a method approved in accordance with the procedures specified in paragraph (j) of this AD. We have revised subsequent paragraph identifiers accordingly. This difference has been coordinated with Boeing. Request for Clarification of Follow-On Actions Boeing requested that we reword paragraph (g) of the NPRM (77 FR 36222, June 18, 2012) to clarify the follow-on actions required after the inspections. Boeing stated that the requirement to continue repetitive inspections needs to be clarified since it only pertains if the hinges were found to be uncracked. We agree that clarification is needed. The repetitive inspections are not required if the modification has been accomplished with hinges having P/Ns 113A8341–9 and 113A8341–10. However, the repetitive inspections are required if hinges having P/N 113A8341–1 and 113A8341–2 are installed. We have added this clarification in paragraphs (g)(1) and (g)(2) of this AD. Request To Require Modification of Only Doors Having Cracked Hinges Southwest Airlines (Southwest) requested that replacement of the hinges be required only on the door where cracks were found, rather than replacing both doors if cracking is found only on one door. Southwest stated it wants the option to not modify a door on which the hinges are not cracked, even though there is hinge cracking on the door on the other side of the airplane. Southwest added that, for a door that has no cracked hinges, the repetitive inspections would remain effective, and modification would not be required prior to further flight. We agree that only doors with cracked hinges need to be modified, and that the repetitive inspections specified in the AD remain in effect for the door that has not been modified. We have revised paragraph (g)(2)(i) of this AD to clarify that modification is only required on affected doors. Request for the Option To Remove Inboard MLG Door in Accordance With the Configuration Deviation List (CDL) Southwest requested that we allow the option of removing the inboard MLG door from the airplane as specified in the CDL. Southwest noted that the CDL allows for continued operation without the inboard MLG door. We agree with adding an option to the AD to remove the affected inboard MLG door. However, the removal must be done in accordance with a method approved by the FAA because applicable flight effects and restrictions must be accounted for. In addition, if a door with new hinge fittings is reinstalled, the inspection required by paragraph (h) of this AD must be done. We have added paragraph (g)(2)(ii) of this AD accordingly. We have also added note 1 to paragraph (g)(2)(ii) of this AD to this AD to refer to the CDL as guidance. Supplemental Type Certificate (STC) Winglet Comment rgstc.nsf/0/408E012E008616A786 2578880060456C?OpenDocument& Highlight=st00830se) does not affect the accomplishment of the manufacturer’s service instructions. We have added paragraph (c)(1) to this AD to state that installation of STC ST00830SE (https://rgl.faa.gov/ Regulatory_and_Guidance_Library/ rgstc.nsf/0/408E012E008616A78625788 80060456C?OpenDocument& Highlight=st00830se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE 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. For all other AMOC requests, the operator must request approval of an AMOC in accordance with the procedures specified in paragraph (j) of this AD. New Optional Installation Paragraph We have added new paragraph (h)(1) to this AD to clarify that installing new MLG door hinge fittings having P/N 113A8341–9 and 113A8341–10, terminates the inspection requirements of this AD for only the door on which new fittings are installed. 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 (77 FR 36222, June 18, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 36222, June 18, 2012). 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 Aviation Partners Boeing stated that the installation of winglets per STC ST00830SE (https://rgl.faa.gov/ Regulatory_and_Guidance_Library/ We estimate that this AD affects 1,175 airplanes of U.S. registry. We estimate the following costs to comply with this AD: tkelley on DSK3SPTVN1PROD with RULES ESTIMATED COSTS Action Labor cost Parts cost Inspection ....................... 3 work-hours × $85 per hour = $255 per inspection cycle. $0 VerDate Mar<15>2010 17:24 Aug 15, 2013 Jkt 229001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Cost per product $255 per inspection cycle. E:\FR\FM\16AUR1.SGM 16AUR1 Cost on U.S. operators $299,625 per inspection cycle. Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations We estimate the following costs to do any necessary modification that would be required based on the results of the inspection. We have no way of 49905 determining the number of airplanes that might need this modification: ON-CONDITION COSTS Action Labor cost Parts cost Modification ................................ 9 work-hours × $85 per hour = $765 .......................................... $6,550 According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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. tkelley on DSK3SPTVN1PROD with RULES Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. VerDate Mar<15>2010 17:24 Aug 15, 2013 Jkt 229001 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 adding the following new airworthiness directive (AD): ■ 2013–15–16 The Boeing Company: Amendment 39–17532; Docket No. FAA–2012–0637; Directorate Identifier 2012–NM–006–AD. (a) Effective Date This AD is effective September 20, 2013. (b) Affected ADs None. (c) Applicability (1) This AD applies to The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. (2) Installation of Supplemental Type Certificate (STC) ST00830SE (https://rgl.faa. gov/Regulatory_and_Guidance_Library/rgstc. nsf/0/408E012E008616A7862578880060 456C?OpenDocument&Highlight=st00830se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE 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 Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 52, Doors. (e) Unsafe Condition This AD was prompted by a report of an inboard main landing gear (MLG) door assembly departure due to premature fatigue cracking in the inboard MLG door hinge PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Cost per product $7,315 fittings. We are issuing this AD to detect and correct fatigue cracking in the inboard MLG door hinge fittings, which could result in loss of the MLG door assembly from the airplane, and the MLG door assembly could impact the flight control surfaces and result in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Initial and Repetitive Inspections Except as provided by paragraph (i) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011, do either a detailed or surface high frequency eddy current (HFEC) inspection for cracking of the left- and rightside inboard MLG door hinge fittings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. (1) If no cracking is found, at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011, do the actions specified in either paragraph (g)(1)(i) or (g)(1)(ii) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. (i) Repeat either a detailed or a surface HFEC inspection for cracking of the left- and right-side inboard MLG door hinge fittings. (ii) Modify the hinge fittings on the inboard MLG doors by installing P/N 113A8341–9 and 113A8341–10, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. Doing the modification specified in this paragraph terminates the inspection requirements for only the door on which new fittings are installed. (2) If any cracking is found, before further flight, do the actions specified in either paragraph (g)(2)(i) or (g)(2)(ii) of this AD. (i) Modify the hinge fittings on all affected inboard MLG doors by installing P/N 113A8341–9 and 113A8341–10, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. Doing the modification specified in this paragraph terminates the inspection requirements for only the door on which new fittings are installed. (ii) Remove the affected MLG door, using a method approved in accordance with the procedures specified in paragraph (j) of this AD. For airplanes on which this door is reinstalled, before further flight, accomplish the actions specified in either paragraph E:\FR\FM\16AUR1.SGM 16AUR1 49906 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations (h)(1) or (h)(2) of this AD on the reinstalled door. Note 1 to paragraph (g)(2)(ii) of this AD: Guidance for removing the door can be found in Section 32–10 of Appendix CDL, Configuration Deviation List, Model 737– 100/200/300/400/500/600/700/800/900/900 ER Series, to the Boeing 737–700 Airplane Flight Manual Document D631A001. (h) Optional Installation (1) Installing new MLG door hinge fittings having P/N 113A8341–9 and 113A8341–10, terminates the inspection requirements of this AD for only the doors on which new fittings are installed. (2) Installing new MLG door hinge fittings having P/N 113A8341–1 and 113A8341–2, is acceptable for compliance with the modification specified in paragraphs (g)(1)(ii) and (g)(2)(i) of this AD, provided the inspections (both the initial and the repetitive inspections) required by paragraph (g) of this AD are done within the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. Installation of the MLG door hinge fittings having P/N 113A8341–1 and 113A8341–2, as applicable, must be done using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Accomplishing the requirements of this paragraph does not terminate the inspection requirements of paragraph (g) of this AD. tkelley on DSK3SPTVN1PROD with RULES (i) Exception to the Service Information Where Boeing Alert Service Bulletin 737– 52A1167, dated December 1, 2011, 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. (j) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-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, 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. VerDate Mar<15>2010 17:24 Aug 15, 2013 Jkt 229001 (k) Related Information For more information about this AD, contact Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6440; fax: 425–917–6590; email: nancy.marsh@faa.gov. (l) 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. (i) Boeing Alert Service Bulletin 737– 52A1167, dated December 1, 2011. (ii) Reserved. (3) 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. (4) You may view this service information at 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. (5) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on July 21, 2013. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–18090 Filed 8–15–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0361; Directorate Identifier 2013–NM–026–AD; Amendment 39–17527; AD 2013–15–11] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by a report of cracking in the left-side chord of the fin SUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 closure rib on the vertical stabilizer. This AD requires repetitive inspections of the left and right side chords of the fin closure rib for cracking and corrosion, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking and corrosion in the left- and right-side chords of the fin closure rib, which could lead to widespread cracking in the chords that might weaken the fin closure rib structure and result in loss of airplane control due to lack of horizontal stabilizer support. DATES: This AD is effective September 20, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 20, 2013. 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 review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6577; fax: 425–917–6590; email: berhane.alazar@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. The NPRM published in the Federal E:\FR\FM\16AUR1.SGM 16AUR1

Agencies

[Federal Register Volume 78, Number 159 (Friday, August 16, 2013)]
[Rules and Regulations]
[Pages 49903-49906]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18090]



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

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

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

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


Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules 
and Regulations

[[Page 49903]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0637; Directorate Identifier 2012-NM-006-AD; 
Amendment 39-17532; AD 2013-15-16]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER 
series airplanes. This AD was prompted by a report of an inboard main 
landing gear (MLG) door assembly departure due to premature fatigue 
cracking in the inboard MLG door hinge fittings. This AD requires 
repetitive inspections for cracking of the inboard MLG door hinge 
fittings; and replacement or modification of cracked fittings. This AD 
also provides an option to remove the affected MLG door. We are issuing 
this AD to detect and correct fatigue cracking in the inboard MLG door 
hinge fittings, which could result in loss of the MLG door assembly 
from the airplane, and the MLG door assembly could impact the flight 
control surfaces and result in reduced controllability of the airplane.

DATES: This AD is effective September 20, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 20, 
2013.

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

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
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 include an AD that would apply to the specified products. 
The NPRM published in the Federal Register on June 18, 2012 (77 FR 
36222). The NPRM proposed to require repetitive inspections for 
cracking of the inboard MLG door hinge fittings; and modification of 
cracked fittings, which would terminate the repetitive inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 36222, June 18, 2012) and the FAA's response to each comment.

Request To Extend Compliance Time

    American Airlines requested that we revise the NPRM (77 FR 36222, 
June 18, 2012) to extend the compliance time for the initial 
inspections from 10,000 total flight cycles to before 18,000 total 
flight cycles. American Airlines stated that the FAA has not provided 
sufficient evidence to warrant issuance of regulatory action with such 
a reduced compliance time. American Airlines calculated that the event 
described in the service information represents only 0.085 percent of 
the airplanes under U.S. registry, and that the event described 
occurred at 24,000 total flight cycles.
    We disagree with the request to extend the compliance time. In 
developing an appropriate compliance time for this action, we 
considered the safety implications, parts availability, and normal 
maintenance schedules for the timely accomplishment of the inspections 
and modifications. There is additional data related to the MLG door 
hinge failures that is not included in the manufacturer's service 
bulletin. Up to 10 percent of hinges inspected to date have been found 
with cracking. The cracking occurred between 11,000 and 24,000 total 
flight cycles, and has been found on both hinges of the inboard MLG 
door. In consideration of these items, we have determined that a 
compliance time of before 10,000 total flight cycles will ensure an 
acceptable level of safety and allow the inspections and modifications 
to be done during scheduled maintenance intervals for most affected 
operators. We have not changed the AD in this regard.

Request To Allow New Hinges Having Part Numbers (P/Ns) 113A8341-1 and 
113A8341-2

    American Airlines requested that we revise paragraph (g) of the 
NPRM (77 FR 36222, June 18, 2012) to allow installation of new hinges 
having P/Ns 113A8341-1 and 113A8341-2 as replacements for cracked 
hinges found during the inspections. American Airlines stated that 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-
52A1167, dated December 1, 2011 (referred to in the NPRM as the 
appropriate source of service information), implies that an operator 
may install a new set of hinges having P/Ns 113A8341-1 and 113A8341-2 
and restart the inspection threshold and

[[Page 49904]]

interval; however, the Accomplishment Instructions recommend 
installation of new hinges having P/Ns 113A8341-9 and 113A8341-10 if 
cracking is found. American Airlines stated that installation of a new 
set of hinges having P/Ns 113A8341-1 and 113A8341-2 should be 
acceptable as long as the on-going repetitive inspections are 
accomplished as defined in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-52A1167, dated December 1, 2011.
    We agree to allow replacement of cracked hinges with new hinges 
having P/Ns 113A8341-1 and 113A8341-2, as long as inspections of the 
replacement hinges are accomplished at the time specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-52A1167, 
dated December 1, 2011. We have added new paragraph (h)(2) to this AD 
to clarify that installing new MLG door hinge fittings having P/N 
113A8341-1 and 113A8341-2, is acceptable for compliance with the 
modification specified in paragraphs (g)(1)(ii) and (g)(2)(i) of this 
AD. Paragraph (h)(2) also specifies that installation of the MLG door 
hinge fittings having P/N 113A8341-1 and 113A8341-2, must be done using 
a method approved in accordance with the procedures specified in 
paragraph (j) of this AD. We have revised subsequent paragraph 
identifiers accordingly. This difference has been coordinated with 
Boeing.

Request for Clarification of Follow-On Actions

    Boeing requested that we reword paragraph (g) of the NPRM (77 FR 
36222, June 18, 2012) to clarify the follow-on actions required after 
the inspections. Boeing stated that the requirement to continue 
repetitive inspections needs to be clarified since it only pertains if 
the hinges were found to be uncracked.
    We agree that clarification is needed. The repetitive inspections 
are not required if the modification has been accomplished with hinges 
having P/Ns 113A8341-9 and 113A8341-10. However, the repetitive 
inspections are required if hinges having P/N 113A8341-1 and 113A8341-2 
are installed. We have added this clarification in paragraphs (g)(1) 
and (g)(2) of this AD.

Request To Require Modification of Only Doors Having Cracked Hinges

    Southwest Airlines (Southwest) requested that replacement of the 
hinges be required only on the door where cracks were found, rather 
than replacing both doors if cracking is found only on one door. 
Southwest stated it wants the option to not modify a door on which the 
hinges are not cracked, even though there is hinge cracking on the door 
on the other side of the airplane. Southwest added that, for a door 
that has no cracked hinges, the repetitive inspections would remain 
effective, and modification would not be required prior to further 
flight.
    We agree that only doors with cracked hinges need to be modified, 
and that the repetitive inspections specified in the AD remain in 
effect for the door that has not been modified. We have revised 
paragraph (g)(2)(i) of this AD to clarify that modification is only 
required on affected doors.

Request for the Option To Remove Inboard MLG Door in Accordance With 
the Configuration Deviation List (CDL)

    Southwest requested that we allow the option of removing the 
inboard MLG door from the airplane as specified in the CDL. Southwest 
noted that the CDL allows for continued operation without the inboard 
MLG door.
    We agree with adding an option to the AD to remove the affected 
inboard MLG door. However, the removal must be done in accordance with 
a method approved by the FAA because applicable flight effects and 
restrictions must be accounted for. In addition, if a door with new 
hinge fittings is reinstalled, the inspection required by paragraph (h) 
of this AD must be done. We have added paragraph (g)(2)(ii) of this AD 
accordingly. We have also added note 1 to paragraph (g)(2)(ii) of this 
AD to this AD to refer to the CDL as guidance.

Supplemental Type Certificate (STC) Winglet Comment

    Aviation Partners Boeing stated that the installation of winglets 
per STC ST00830SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) does 
not affect the accomplishment of the manufacturer's service 
instructions.
    We have added paragraph (c)(1) to this AD to state that 
installation of STC ST00830SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) does 
not affect the ability to accomplish the actions required by this AD. 
Therefore, for airplanes on which STC ST00830SE 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. For all other AMOC requests, the operator must request approval 
of an AMOC in accordance with the procedures specified in paragraph (j) 
of this AD.

New Optional Installation Paragraph

    We have added new paragraph (h)(1) to this AD to clarify that 
installing new MLG door hinge fittings having P/N 113A8341-9 and 
113A8341-10, terminates the inspection requirements of this AD for only 
the door on which new fittings are installed.

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 (77 FR 36222, June 18, 2012) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 36222, June 18, 2012).
    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 1,175 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
----------------------------------------------------------------------------------------------------------------
Inspection......................  3 work-hours x $85 per           $0   $255 per inspection  $299,625 per
                                   hour = $255 per                       cycle.               inspection cycle.
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 49905]]

    We estimate the following costs to do any necessary modification 
that would be required based on the results of the inspection. We have 
no way of determining the number of airplanes that might need this 
modification:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                             Labor cost            Parts cost       Cost per product
----------------------------------------------------------------------------------------------------------------
Modification...........................  9 work-hours x $85 per hour =       $6,550   $7,315
                                          $765.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

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

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2013-15-16 The Boeing Company: Amendment 39-17532; Docket No. FAA-
2012-0637; Directorate Identifier 2012-NM-006-AD.

(a) Effective Date

    This AD is effective September 20, 2013.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 737-
52A1167, dated December 1, 2011.
    (2) Installation of Supplemental Type Certificate (STC) 
ST00830SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST00830SE 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

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 52, Doors.

(e) Unsafe Condition

    This AD was prompted by a report of an inboard main landing gear 
(MLG) door assembly departure due to premature fatigue cracking in 
the inboard MLG door hinge fittings. We are issuing this AD to 
detect and correct fatigue cracking in the inboard MLG door hinge 
fittings, which could result in loss of the MLG door assembly from 
the airplane, and the MLG door assembly could impact the flight 
control surfaces and result in reduced controllability of the 
airplane.

(f) Compliance

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

(g) Initial and Repetitive Inspections

    Except as provided by paragraph (i) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-52A1167, dated December 1, 2011, 
do either a detailed or surface high frequency eddy current (HFEC) 
inspection for cracking of the left- and right-side inboard MLG door 
hinge fittings, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-52A1167, dated December 1, 
2011.
    (1) If no cracking is found, at the times specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-52A1167, 
dated December 1, 2011, do the actions specified in either paragraph 
(g)(1)(i) or (g)(1)(ii) of this AD, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1167, dated December 1, 2011.
    (i) Repeat either a detailed or a surface HFEC inspection for 
cracking of the left- and right-side inboard MLG door hinge 
fittings.
    (ii) Modify the hinge fittings on the inboard MLG doors by 
installing P/N 113A8341-9 and 113A8341-10, in accordance with Part 3 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-52A1167, dated December 1, 2011. Doing the modification 
specified in this paragraph terminates the inspection requirements 
for only the door on which new fittings are installed.
    (2) If any cracking is found, before further flight, do the 
actions specified in either paragraph (g)(2)(i) or (g)(2)(ii) of 
this AD.
    (i) Modify the hinge fittings on all affected inboard MLG doors 
by installing P/N 113A8341-9 and 113A8341-10, in accordance with 
Part 3 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-52A1167, dated December 1, 2011. Doing the modification 
specified in this paragraph terminates the inspection requirements 
for only the door on which new fittings are installed.
    (ii) Remove the affected MLG door, using a method approved in 
accordance with the procedures specified in paragraph (j) of this 
AD. For airplanes on which this door is reinstalled, before further 
flight, accomplish the actions specified in either paragraph

[[Page 49906]]

(h)(1) or (h)(2) of this AD on the reinstalled door.

    Note 1 to paragraph (g)(2)(ii) of this AD: Guidance for removing 
the door can be found in Section 32-10 of Appendix CDL, 
Configuration Deviation List, Model 737-100/200/300/400/500/600/700/
800/900/900 ER Series, to the Boeing 737-700 Airplane Flight Manual 
Document D631A001.

(h) Optional Installation

    (1) Installing new MLG door hinge fittings having P/N 113A8341-9 
and 113A8341-10, terminates the inspection requirements of this AD 
for only the doors on which new fittings are installed.
    (2) Installing new MLG door hinge fittings having P/N 113A8341-1 
and 113A8341-2, is acceptable for compliance with the modification 
specified in paragraphs (g)(1)(ii) and (g)(2)(i) of this AD, 
provided the inspections (both the initial and the repetitive 
inspections) required by paragraph (g) of this AD are done within 
the applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-52A1167, dated December 1, 2011. 
Installation of the MLG door hinge fittings having P/N 113A8341-1 
and 113A8341-2, as applicable, must be done using a method approved 
in accordance with the procedures specified in paragraph (j) of this 
AD. Accomplishing the requirements of this paragraph does not 
terminate the inspection requirements of paragraph (g) of this AD.

(i) Exception to the Service Information

    Where Boeing Alert Service Bulletin 737-52A1167, dated December 
1, 2011, 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.

(j) 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 the Related Information 
section 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, 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.

(k) Related Information

    For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6440; fax: 425-917-6590; email: nancy.marsh@faa.gov.

(l) 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.
    (i) Boeing Alert Service Bulletin 737-52A1167, dated December 1, 
2011.
    (ii) Reserved.
    (3) 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.
    (4) You may view this service information at 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.
    (5) 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 21, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-18090 Filed 8-15-13; 8:45 am]
BILLING CODE 4910-13-P

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