83 FR 22422 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 94 (May 15, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 94 (May 15, 2018)
| Page Range | 22422-22426 | |
| FR Document | 2018-10299 |
[Federal Register Volume 83, Number 94 (Tuesday, May 15, 2018)] [Proposed Rules] [Pages 22422-22426] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-10299] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0412; Product Identifier 2017-NM-180-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2010-25- 06, which applies to certain The Boeing Company Model 737-200, -300, - 400, and -500 series airplanes. AD 2010-25-06 requires repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. AD 2010-25-06 also provides for an optional repair, which terminates the repetitive inspections. For airplanes on which a certain repair is done, AD 2010-25-06 also requires repetitive inspections for cracking of certain fuselage frames and stub beams, [[Page 22423]] and corrective actions if necessary. Since we issued AD 2010-25-06, additional cracking was found in areas not covered by the inspections. This proposed AD would retain the actions required by AD 2010-25-06 and would expand the inspection area. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 29, 2018. 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 NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0412. 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-2018- 0412; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800-647- 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627- 5210; email: [email protected]. 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-2018-0412; Product Identifier 2017-NM-180-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 issued AD 2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010) (``AD 2010-25-06''), for certain Model 737-200, -300, -400, and -500 series airplanes. AD 2010-25-06 requires repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. AD 2010-25-06 also provides for an optional repair, which terminates the repetitive inspections. For airplanes on which a certain repair is done, AD 2010-25-06 also requires repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. AD 2010-25-06 resulted from reports of the detection of fatigue cracks at certain frame sections, in addition to stub beam cracking, caused by high flight cycle stresses from both pressurization and maneuver loads. We issued AD 2010-25-06 to detect and correct fatigue cracking of certain fuselage frames and stub beams and possible severed frames, which could result in reduced structural integrity of the frames. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and could result in rapid decompression of the fuselage. Actions Since AD 2010-25-06 Was Issued Since we issued AD 2010-25-06, additional cracking was found in areas not covered by the inspections. During an inspection of the body station (BS) 616 stub beam upper chord, an operator identified additional cracking at buttock line (BL) 64. We determined that eddy current inspections of the upper chord at BL 64 and BL 65 must be done to maintain structural integrity. In addition, during inspections of the longitudinal floor beam web at the BS 639 stub beams operators found cracking in the floor beam web. It was determined that the inspections required by AD 2010-25-06 were inadequate, and eddy current inspections of the BL 45.5 floor beam web at the BS 639 stub beam interface must be done to address this cracking. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. The service information describes procedures for detailed and eddy current inspections of the fuselage frame and over wing stub beam at BS 616, BS 639, and BS 597 or BS 601, and BL 45.5 floor beam web at the BS 639 stub beam attachment, and relative investigative and corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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 retain all requirements of AD 2010-25-06. This proposed AD does not explicitly restate the requirements of AD 2010-25-06. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in this proposed AD, except for any differences identified as exceptions in the regulatory text of this proposed AD. This proposed AD would add new repetitive inspections for cracking of certain other fuselage frames and stub beams. 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-2018-0412. Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, provides two economic inspections to find cracking prior to frame damage, which could require extensive repairs. These inspections are recommended but are not mandated in this proposed AD. [[Page 22424]] The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Costs of Compliance We estimate that this proposed AD affects 67 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections..................... Up to 67 $0 Up to $5,695 per Up to $381,565 per work[dash]hours x inspection cycle. inspection cycle. $85 per hour = $5,695. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do certain necessary repairs/ replacements that would be required based on the results of the proposed inspections. We have no way of determining the number of aircraft that might need these repairs/replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action ** Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repairs/replacements.................. Up to 76 work[dash]hours * Up to $6,460. x $85 per hour = $6,460. ---------------------------------------------------------------------------------------------------------------- * All required parts are supplied by the operator. This cost is minimal, and we have no way to determine what an operator would pay for these parts. ** We have received no definitive data that would enable us to provide cost estimates for certain other repairs specified in this proposed AD. 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We have 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 that the 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, 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 removing Airworthiness Directive (AD) 2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010), and adding the following new AD: The Boeing Company: Docket No. FAA-2018-0412; Product Identifier 2017-NM-180-AD. (a) Comments Due Date The FAA must receive comments on this AD action by June 29, 2018. (b) Affected ADs This AD replaces AD 2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010) (``AD 2010-25-06''). (c) Applicability This AD applies to The Boeing Company Model 737-200, -300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by the detection of fatigue cracks at certain frame sections, in addition to stub beam cracking, caused by high flight cycle stresses from both pressurization and maneuver loads and additional cracking found in areas not covered by the inspections in AD 2010-25-06. We are issuing this AD to address fatigue cracking of certain fuselage frames and stub beams and possible severed frames, which could result in reduced structural integrity of the frames. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and [[Page 22425]] could result in rapid decompression of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of Body Stations 616 and 639 Frames and Stub Beams and Corrective Actions At the applicable time specified table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017: Do a detailed or high frequency eddy current (HFEC) inspection for cracking of the body station (BS) 616 and 639 frames and stub beams and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the inspection at the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (h) Repetitive Post-Repair Inspections of Body Stations 616 and 639 Frames and Integral Stub Beams and Corrective Actions At the applicable time specified table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017: Do the inspections required by paragraphs (h)(1) and (h)(2) of this AD; or the inspection required by paragraph (h)(3) of this AD; as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the inspection at the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (1) Do a low frequency eddy current (LFEC) inspection of the web, and an HFEC inspection of the inner and outer chord common to the upper end fastener rows of the web splice doubler for cracking. (2) Do the inspection specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD. (i) Do a detailed inspection of the replacement frame section for cracking. (ii) Do an HFEC and LFEC inspection of the replacement frame section for cracking. (3) Do a detailed or HFEC inspection of the replacement stub beam for cracking. (i) Repetitive Inspections of Buttock Line 45.5 Longitudinal Floor Beam Web at Body Station 639 Stub Beam Attachment and Corrective Actions For Group 1 and Group 2 airplanes as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the time specified table 3 or table 4, as applicable, of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(2) of this AD: Do the inspections required by paragraph (i)(1) and (i)(2) of this AD and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable corrective actions before further flight. Thereafter, repeat the inspections at the time specified in table 3 or table 4, as applicable, of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (1) Do an open-hole HFEC inspection for cracking of the buttock line (BL) 45.5 longitudinal floor beam web at each fastener hole common to the stub beam attachment angle. (2) Do an HFEC surface inspection for cracking of the BL 45.5 longitudinal floor beam web around the fastener head/tail at each fastener location common to the backup strap. (j) Repetitive Post-Repair Inspections of Buttock Line 45.5 Longitudinal Floor Beam Web at Body Station 639 and Corrective Actions For Group 2 airplanes as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the applicable time specified table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(2) of this AD: Do the inspections required by paragraphs (j)(1) and (j)(2) of this AD and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable corrective actions before further flight. Thereafter, repeat the inspections at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (1) Do an open-hole HFEC inspection for cracking of the BL 45.5 longitudinal floor beam web filler at each fastener hole common to the stub beam attachment angle. (2) Do an HFEC surface inspection for cracking of the BL 45.5 longitudinal floor beam web filler around the fastener head/tail at each fastener location common to the backup strap. (k) Repetitive Inspections for Cracking of BS 616 Machined Stub Beam Upper Chord and Corrective Actions For Group 2 and Group 3 airplanes as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the applicable time specified in table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(2) of this AD; do detailed and medium frequency eddy current subsurface inspections for cracking of the BS 616 machined stub beam upper chord, and all applicable corrective actions, except as required by paragraph (m)(1) of this AD. Do all applicable corrective actions before further flight. Thereafter, repeat the inspections at the applicable time specified in table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD, using Boeing Alert Service Bulletin 737- 53A1254, Revision 1, dated July 9, 2009; or Boeing Alert Service Bulletin 737-53A1254, Revision 2, dated February 22, 2012. (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD, using Boeing Alert Service Bulletin 737- 53A1254, Revision 2, dated February 22, 2012. (m) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, specifies to contact Boeing for repair instructions: Before further flight, do the repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (2) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, specifies a compliance time ``after the Revision 3 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of the person identified in paragraph (o)(1) of this AD. Information may be emailed to: [email protected]. (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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. [[Page 22426]] (4) AMOCs approved previously for AD 2010-25-06 are approved as AMOCs for the corresponding provisions of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, that are required by paragraphs (g) and (h) of this AD. (o) Related Information (1) For information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5324; fax: 562-627-5210; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740- 5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Issued in Des Moines, Washington, on May 8, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-10299 Filed 5-14-18; 8:45 am] BILLING CODE 4910-13-P
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(b) Affected ADs (2) For purposes of determining deviations to RC steps, including substeps
This AD replaces AD 2017–16–05, compliance with the requirements of this AD: and identified figures.
Amendment 39–18982 (82 FR 39344, August Where BASB 737–57A1327, R2 uses the (ii) Operators may deviate from steps not
18, 2017) (‘‘AD 2017–16–05’’). phrase ‘‘the Revision 2 date of this service labeled as RC by using accepted methods in
bulletin,’’ this AD requires using ‘‘the accordance with the operator’s maintenance
(c) Applicability effective date of this AD.’’ or inspection program without obtaining
This AD applies to all The Boeing approval of an AMOC, provided the RC steps,
(i) Parts Installation Limitation including substeps and identified figures, can
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes, As of the effective date of this AD, no still be done as specified, and the airplane
certificated in any category, as specified in person may install a Krueger flap or Krueger can be put back in an airworthy condition.
paragraphs (c)(1) through (c)(3) of this AD. flap bullnose on any airplane, unless the
actions required by paragraph (g) of this AD (l) Related Information
(1) Airplanes in Groups 1 and 2 as
identified in Boeing Alert Service Bulletin have been accomplished on the Krueger flap (1) For more information about this AD,
737–57A1327, Revision 2, dated July 25, bullnose. contact Alan Pohl, Aerospace Engineer,
2017 (‘‘BASB 737–57A1327, R2’’). Airframe Section, FAA, Seattle ACO Branch,
(2) Airplanes in Group 3, as identified in (j) Credit for Previous Actions 2200 South 216th St., Des Moines, WA
BASB 737–57A1327, R2, except where this (1) This paragraph provides credit for the 98198; phone and fax: 206–231–3527; email:
service bulletin specifies the groups as line actions specified in paragraph (g) of this AD, alan.pohl@faa.gov.
numbers 6422 through 6465 inclusive, this if those actions were performed before (2) For service information identified in
AD specifies those groups as line number September 22, 2017 (the effective date of AD this AD, contact Boeing Commercial
6422 through any line number airplane with 2017–16–05), using Boeing Alert Service Airplanes, Attention: Contractual & Data
an original Certificate of Airworthiness or an Bulletin 737–57A1327, dated May 20, 2016. Services (C&DS), 2600 Westminster Blvd.,
original Export Certificate of Airworthiness (2) This paragraph provides credit for the MC 110–SK57, Seal Beach, CA 90740–5600;
dated on or before the effective date of this actions specified in paragraph (g) of this AD, telephone: 562–797–1717; internet: https://
AD. if those actions were performed before the www.myboeingfleet.com. You may view this
(3) All Model 737–600, –700, –700C, –800, effective date of this AD, using Boeing Alert referenced service information at the FAA,
–900 and –900ER series airplanes with an Service Bulletin 737–57A1327, Revision 1, Transport Standards Branch, 2200 South
original Certificate of Airworthiness or an dated September 28, 2016. 216th St., Des Moines, WA. For information
original Export Certificate of Airworthiness on the availability of this material at the
dated after the effective date of this AD. (k) Alternative Methods of Compliance
FAA, call 206–231–3195.
(AMOCs)
(d) Subject (1) The Manager, Seattle ACO Branch, Issued in Des Moines, Washington, on May
Air Transport Association (ATA) of FAA, has the authority to approve AMOCs 7, 2018.
America Code 57, Wings. for this AD, if requested using the procedures Michael Kaszycki,
(e) Unsafe Condition found in 14 CFR 39.19. In accordance with Acting Director, System Oversight Division,
14 CFR 39.19, send your request to your Aircraft Certification Service.
This AD was prompted by a report of a principal inspector or local Flight Standards [FR Doc. 2018–10213 Filed 5–14–18; 8:45 am]
Krueger flap bullnose departing an airplane District Office, as appropriate. If sending
during taxi, which caused damage to the BILLING CODE 4910–13–P
information directly to the manager of the
wing structure and thrust reverser, and a certification office, send it to the attention of
report of a missing no. 2 Krueger flap the person identified in paragraph (l)(1) of
bullnose hinge bolt from an airplane that was this AD. Information may be emailed to: 9- DEPARTMENT OF TRANSPORTATION
not included in the effectivity of AD 2017– ANM-Seattle-ACO-AMOC-Requests@faa.gov.
16–05. We are issuing this AD to address (2) Before using any approved AMOC, Federal Aviation Administration
missing Krueger flap bullnose hardware. notify your appropriate principal inspector,
Such missing hardware could result in the or lacking a principal inspector, the manager 14 CFR Part 39
Krueger flap bullnose departing the airplane of the local flight standards district office/
during flight, which could damage [Docket No. FAA–2018–0412; Product
certificate holding district office.
empennage structure and lead to the inability Identifier 2017–NM–180–AD]
(3) An AMOC that provides an acceptable
to maintain continued safe flight and level of safety may be used for any repair, RIN 2120–AA64
landing. modification, or alteration required by this
(f) Compliance AD if it is approved by the Boeing Airworthiness Directives; The Boeing
Commercial Airplanes Organization Company Airplanes
Comply with this AD within the
Designation Authorization (ODA) that has
compliance times specified, unless already
done. been authorized by the Manager, Seattle ACO AGENCY: Federal Aviation
Branch, to make those findings. To be Administration (FAA), DOT.
(g) Required Actions approved, the repair method, modification ACTION: Notice of proposed rulemaking
For airplanes identified in paragraphs deviation, or alteration deviation must meet
the certification basis of the airplane, and the
(NPRM).
(c)(1) and (c)(2) of this AD: Except as
required by paragraph (h) of this AD, at the approval must specifically refer to this AD.
SUMMARY: We propose to supersede
applicable times specified in paragraph 1.E., (4) AMOCs approved previously for AD
2017–16–05 are approved as AMOCs for the Airworthiness Directive (AD) 2010–25–
‘‘Compliance,’’ of BASB 737–57A1327, R2, 06, which applies to certain The Boeing
do all applicable actions identified as ‘‘RC’’ corresponding provisions of BASB 737–
(required for compliance) in, and in 57A1327, R2 that are required by paragraph Company Model 737–200, –300, –400,
accordance with, the Accomplishment (g) of this AD. and –500 series airplanes. AD 2010–25–
Instructions of BASB 737–57A1327, R2. (5) For service information that contains 06 requires repetitive inspections for
steps that are labeled as RC, the provisions cracking of certain fuselage frames and
daltland on DSKBBV9HB2PROD with PROPOSALS
(h) Exceptions to Service Information of paragraphs (k)(5)(i) and (k)(5)(ii) of this AD stub beams, and corrective actions if
Specifications apply. necessary. AD 2010–25–06 also
(1) For purposes of determining (i) The steps labeled as RC, including
provides for an optional repair, which
compliance with the requirements of this AD: substeps under an RC step and any figures
Where BASB 737–57A1327, R2 uses the identified in an RC step, must be done to terminates the repetitive inspections.
phrase ‘‘the original issue date of this service comply with the AD. If a step or substep is For airplanes on which a certain repair
bulletin,’’ this AD requires using September labeled ‘‘RC Exempt,’’ then the RC is done, AD 2010–25–06 also requires
22, 2017 (the effective date of AD 2017–16– requirement is removed from that step or repetitive inspections for cracking of
05). substep. An AMOC is required for any certain fuselage frames and stub beams,
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The phrase ‘‘corrective actions’’ is Costs of Compliance estimate the following costs to comply
used in this proposed AD. Corrective with this proposed AD:
actions correct or address any condition We estimate that this proposed AD
found. Corrective actions in an AD affects 67 airplanes of U.S. registry. We
could include, for example, repairs.
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections ............................. Up to 67 work-hours × $85 $0 Up to $5,695 per inspection Up to $381,565 per inspection
per hour = $5,695. cycle. cycle.
We estimate the following costs to do results of the proposed inspections. We of aircraft that might need these repairs/
certain necessary repairs/replacements have no way of determining the number replacements:
that would be required based on the
ON-CONDITION COSTS
Action ** Labor cost Parts cost Cost per product
Repairs/replacements .................................................. Up to 76 work-hours × $85 per hour = $6,460 .......... * Up to $6,460.
* All required parts are supplied by the operator. This cost is minimal, and we have no way to determine what an operator would pay for these
parts.
** We have received no definitive data that would enable us to provide cost estimates for certain other repairs specified in this proposed AD.
Authority for This Rulemaking implications under Executive Order § 39.13 [Amended]
Title 49 of the United States Code 13132. This proposed AD would not ■ 2. The FAA amends § 39.13 by
specifies the FAA’s authority to issue have a substantial direct effect on the removing Airworthiness Directive (AD)
rules on aviation safety. Subtitle I, States, on the relationship between the 2010–25–06, Amendment 39–16539 (75
Section 106, describes the authority of national Government and the States, or FR 81409, December 28, 2010), and
the FAA Administrator. Subtitle VII, on the distribution of power and adding the following new AD:
Aviation Programs, describes in more responsibilities among the various The Boeing Company: Docket No. FAA–
detail the scope of the Agency’s levels of government. 2018–0412; Product Identifier 2017–
authority. For the reasons discussed above, I NM–180–AD.
We are issuing this rulemaking under certify that the proposed regulation: (a) Comments Due Date
the authority described in Subtitle VII, (1) Is not a ‘‘significant regulatory
The FAA must receive comments on this
Part A, Subpart III, Section 44701, action’’ under Executive Order 12866, AD action by June 29, 2018.
‘‘General requirements.’’ Under that (2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and (b) Affected ADs
section, Congress charges the FAA with
promoting safe flight of civil aircraft in Procedures (44 FR 11034, February 26, This AD replaces AD 2010–25–06,
1979), Amendment 39–16539 (75 FR 81409,
air commerce by prescribing regulations December 28, 2010) (‘‘AD 2010–25–06’’).
for practices, methods, and procedures (3) Will not affect intrastate aviation
the Administrator finds necessary for in Alaska, and (c) Applicability
safety in air commerce. This regulation (4) Will not have a significant This AD applies to The Boeing Company
is within the scope of that authority economic impact, positive or negative, Model 737–200, -300, -400, and -500 series
because it addresses an unsafe condition on a substantial number of small entities airplanes, certificated in any category, as
that is likely to exist or develop on under the criteria of the Regulatory identified in Boeing Alert Service Bulletin
737–53A1254, Revision 3, dated November
products identified in this rulemaking Flexibility Act. 13, 2017.
action.
List of Subjects in 14 CFR Part 39 (d) Subject
This proposed AD is issued in
accordance with authority delegated by Air transportation, Aircraft, Aviation Air Transport Association (ATA) of
the Executive Director, Aircraft safety, Incorporation by reference, America Code 53, Fuselage.
Certification Service, as authorized by Safety. (e) Unsafe Condition
FAA Order 8000.51C. In accordance The Proposed Amendment This AD was prompted by the detection of
with that order, issuance of ADs is fatigue cracks at certain frame sections, in
normally a function of the Compliance Accordingly, under the authority addition to stub beam cracking, caused by
and Airworthiness Division, but during delegated to me by the Administrator, high flight cycle stresses from both
this transition period, the Executive the FAA proposes to amend 14 CFR part pressurization and maneuver loads and
daltland on DSKBBV9HB2PROD with PROPOSALS
Director has delegated the authority to 39 as follows: additional cracking found in areas not
issue ADs applicable to transport covered by the inspections in AD 2010–25–
PART 39—AIRWORTHINESS 06. We are issuing this AD to address fatigue
category airplanes to the Director of the
DIRECTIVES cracking of certain fuselage frames and stub
System Oversight Division. beams and possible severed frames, which
Regulatory Findings ■ 1. The authority citation for part 39 could result in reduced structural integrity of
the frames. This reduced structural integrity
We have determined that this continues to read as follows: can increase loading in the fuselage skin,
proposed AD would not have federalism Authority: 49 U.S.C. 106(g), 40113, 44701. which will accelerate skin crack growth and
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![22426 Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Proposed Rules
(4) AMOCs approved previously for AD 11.43 and 11.45, by any of the following We will post all comments we
2010–25–06 are approved as AMOCs for the methods: receive, without change, to http://
corresponding provisions of Boeing Alert • Federal eRulemaking Portal: Go to www.regulations.gov, including any
Service Bulletin 737–53A1254, Revision 3,
dated November 13, 2017, that are required
http://www.regulations.gov. Follow the personal information you provide. We
by paragraphs (g) and (h) of this AD. instructions for submitting comments. will also post a report summarizing each
• Fax: 202–493–2251. substantive verbal contact we receive
(o) Related Information • Mail: U.S. Department of about this NPRM.
(1) For information about this AD, contact Transportation, Docket Operations, M–
Galib Abumeri, Aerospace Engineer, Discussion
30, West Building Ground Floor, Room
Airframe Section, Los Angeles ACO Branch, W12–140, 1200 New Jersey Avenue SE, The European Aviation Safety Agency
FAA, 3960 Paramount Boulevard, Lakewood, (EASA), which is the Technical Agent
CA 90712–4137; phone: 562–627–5324; fax: Washington, DC 20590.
562–627–5210; email: galib.abumeri@faa.gov. • Hand Delivery: Deliver to Mail for the Member States of the European
(2) For service information identified in address above between 9 a.m. and 5 Union, has issued EASA AD 2017–0216,
this AD, contact Boeing Commercial p.m., Monday through Friday, except dated October 30, 2017 (referred to after
Airplanes, Attention: Contractual & Data Federal holidays. this as the Mandatory Continuing
Services (C&DS), 2600 Westminster Blvd., For service information identified in Airworthiness Information, or ‘‘the
MC 110–SK57, Seal Beach, CA 90740–5600; this NPRM, contact Airbus, MCAI’’), to correct an unsafe condition
telephone 562–797–1717; internet https:// for certain Airbus Model A319–115 and
www.myboeingfleet.com. You may view this
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac –132 airplanes, and Model A320–214,
referenced service information at the FAA,
Transport Standards Branch, 2200 South Cedex, France; telephone: +33 5 61 93 –216, –232, and –233 airplanes. The
216th St., Des Moines, WA. For information 36 96; fax: +33 5 61 93 44 51; email: MCAI states:
on the availability of this material at the account.airworth-eas@airbus.com; Airbus introduced mod 154327 on A319
FAA, call 206–231–3195. internet: http://www.airbus.com. You and A320 aeroplanes which substituted the
may view this service information at the pump fuel feed system from the centre fuel
Issued in Des Moines, Washington, on May tank with a jet pump transfer system, based
8, 2018. FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For on the Airbus A321 design. Following the
Jeffrey E. Duven, modification introduction, it was discovered
information on the availability of this that the modified aeroplanes do not have
Director, System Oversight Division, Aircraft
Certification Service.
material at the FAA, call 206–231–3195. electrical ground signals that replicate those
Examining the AD Docket from the deleted centre tank pump pressure
[FR Doc. 2018–10299 Filed 5–14–18; 8:45 am]
switches. These signals are used as part of
BILLING CODE 4910–13–P You may examine the AD docket on the fuel recirculation inhibition request logic.
the internet at http:// Subsequent investigation determined that
www.regulations.gov by searching for ground wires had not been installed on the
DEPARTMENT OF TRANSPORTATION fuel level sensor control units (FLSCU) of
and locating Docket No. FAA–2018–
post-mod aeroplanes, due to a drawing error
Federal Aviation Administration 0411; or in person at the Docket on the fuel system recirculation principle
Management Facility between 9 a.m. diagram. Without these ground wires
14 CFR Part 39 and 5 p.m., Monday through Friday, providing inputs, the FLSCU logic is not
except Federal holidays. The AD docket correctly implemented for gravity feeding
[Docket No. FAA–2018–0411; Product contains this NPRM, the regulatory operation.
Identifier 2017–NM–157–AD] evaluation, any comments received, and This condition, if not corrected, could lead
RIN 2120–AA64 other information. The street address for to reduced fuel pressure at the engine inlet,
the Docket Operations office (telephone: possibly resulting in an uncommanded in-
Airworthiness Directives; Airbus flight shut-down when flying at the gravity
800–647–5527) is in the ADDRESSES feed ceiling levels, as defined in the Aircraft
Airplanes section. Comments will be available in Flight Manual (AFM).
AGENCY: Federal Aviation the AD docket shortly after receipt. To address this potential unsafe condition,
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT: Airbus issued AFM Temporary Revision (TR)
Sanjay Ralhan, Aerospace Engineer, 695 Issue 1 and AFM TR 699 Issue 1 to
ACTION: Notice of proposed rulemaking
International Section, Transport prohibit the use of Jet B and JP4 fuel, and
(NPRM). AFM TR 700 Issue 1 to provide instructions
Standards Branch, FAA, 2200 South for amendment of the gravity feed procedure
SUMMARY: We propose to adopt a new 216th St., Des Moines, WA 98198; for the other fuels.
airworthiness directive (AD) for certain telephone and fax: 206–231–3223. Consequently, EASA issued AD 2016–0205
Airbus Model A319–115 and –132 SUPPLEMENTARY INFORMATION: [which corresponds to FAA AD 2016–25–23,
airplanes, and Model A320–214, –216, Amendment 39–18749 (81 FR 90971,
–232, and –233 airplanes. This proposed Comments Invited December 16, 2016) (‘‘AD 2016–25–23’’)],
AD was prompted by a report indicating We invite you to send any written requiring amendment of the applicable AFM
that certain modified airplanes do not to include the new gravity feed procedure
relevant data, views, or arguments about and to reduce the list of authorised fuels.
have electrical ground wires on the fuel this proposal. Send your comments to Since that [EASA] AD was issued, Airbus
level sensing control unit (FLSCU), an address listed under the ADDRESSES developed a wiring modification to restore
which adversely affects the fuel gravity section. Include ‘‘Docket No. FAA– the intended FLSCU logic, and issued
feeding operation. This proposed AD 2018–0411; Product Identifier 2017– Service Bulletin (SB) A320–28–1242, later
daltland on DSKBBV9HB2PROD with PROPOSALS
would require modification of the NM–157–AD’’ at the beginning of your revised, providing instructions to modify
FLSCU wiring. We are proposing this comments. We specifically invite affected aeroplanes.
AD to address the unsafe condition on comments on the overall regulatory, For the reason described above, this
these products. [EASA] AD retains the requirements of EASA
economic, environmental, and energy AD 2016–0205, which is superseded, and
DATES: We must receive comments on aspects of this NPRM. We will consider requires modification of FLSCU wiring. This
this proposed AD by June 29, 2018. all comments received by the closing [EASA] AD also allows, after that
ADDRESSES: You may send comments, date and may amend this NPRM based modification, to remove the previously
using the procedures found in 14 CFR on those comments. inserted AFM TR’s from the applicable AFM.
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Document Created: 2018-05-15 00:33:51
Document Modified: 2018-05-15 00:33:51
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 29, 2018. | |
| Contact | Galib Abumeri, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627- 5210; email: [email protected] | |
| FR Citation | 83 FR 22422 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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