Airworthiness Directives; The Boeing Company Airplanes, 22763-22766 [2017-10031]

Download as PDF Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0473; Directorate Identifier 2016–NM–195–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This proposed AD was prompted by a report indicating that wear of the bearing plate slider bushings could cause disconnection of certain elevator hinges, which could excite the horizontal stabilizer under certain inflight speed/altitude conditions and lead to degradation of the structure. This proposed AD would require repetitive inspections and checks of certain elevator hinges and related components, repetitive replacements and tests of the bearing plate, and related investigative and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 3, 2017. 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 referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., jstallworth on DSK7TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0473. 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–2017– 0473; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Lu Lu, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6478; fax: 425– 917–6590; email: lu.lu@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0473; Directorate Identifier 2016– NM–195–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received a report indicating that analysis following a special certification review of the horizontal stabilizer determined that wear of the bearing plate slider bushings could cause disconnection of elevator hinge number 4 or number 6. This disconnection could excite the horizontal stabilizer under certain inflight speed/altitude conditions and PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 22763 lead to degradation of the structure due to tab flutter, hinge wear, spar chord corrosion, hinge rib web chafing, hinge rib chord cracking, and inspar lower skin cracking. One or more of these conditions, if not corrected, could result in heavy airplane vibration and damage, which could lead to departure of the elevator and/or horizontal stabilizer from the airplane, and loss of continued safe flight and landing. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016. The service information describes procedures for repetitive inspections and checks of elevator hinge numbers 4 and 6 and related components, repetitive replacements and tests of the bearing plate, and related 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 require accomplishing the actions specified in the service information identified previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ 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–2017– 0473. The phrase ‘‘related investigative actions’’ is used in this proposed AD. Related investigative actions are followon actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ‘‘corrective actions’’ is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. E:\FR\FM\18MYP1.SGM 18MYP1 22764 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737– 55A1099, Revision 1, dated October 21, 2016, specifies to contact the manufacturer for certain instructions, but this proposed AD would require using repair methods, modification deviations, and alteration deviations in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 192 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Elevator hinge high frequency eddy current (HFEC) inspection, loose bolt check. Horizontal stabilizer HFEC and low frequency eddy current (LFEC) inspection, loose bolt check. Horizontal stabilizer detailed corrosion inspection. Elevator general visual inspection for ply damage. 15 work-hours × $85 per hour = $1,275 per inspection/ check cycle. 13 work-hours × $85 per hour = $1,105 per inspection/ check cycle. $0 $1,275 per inspection/check cycle. $244,800 per inspection/ check cycle. 0 $1,105 per inspection/check cycle. $212,160 per inspection/ check cycle. 5 work-hours × 85 per hour = 425 per inspection cycle. Up to 4 work-hours × 85 per hour = 340 per inspection cycle. Up to 6 work-hours × 85 per hour = 510 per inspection cycle. Up to 20 work-hours × 85 per hour = 1,700 per replacement/test cycle. Up to 5 work-hours × 85 per hour = 425 per inspection cycle. 0 $425 per inspection cycle ...... $81,600 per inspection cycle. 0 Up to $340 per inspection cycle. Up to $65,280 per inspection cycle. 0 Up to $510 per inspection cycle. Up to $97,920 per inspection cycle. 4,860 Up to $6,560 per replacement/test cycle. Up to $1,259,520 per replacement/test cycle. 0 Up to $425 per inspection cycle. Up to $81,600 per inspection cycle. Elevator skin tap test inspection for delamination. Elevator hinge bearing plate replacement and binding test. Elevator hinge fitting HFEC inspection. We estimate the following costs to do any necessary related investigative and corrective actions that would be Parts cost Cost per product required based on the results of the proposed inspection. We have no way of Cost on U.S. operators determining the number of aircraft that might need these actions: ON-CONDITION COSTS Labor cost Elevator hinge conditional inspections, measurements, replacements, and repairs. Horizontal stabilizer conditional inspections, replacements, and repairs. 28 work-hours × $85 per hour = $2,380 ......... 1 $0 $2,380 28 work-hours × $85 per hour = $2,380 ......... 10 2,380 1 We have received no definitive data that would enable us to provide cost estimates for the parts for on-condition repairs. Authority for This Rulemaking jstallworth on DSK7TPTVN1PROD with PROPOSALS Parts cost Cost per product Action 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 VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We 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. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. E:\FR\FM\18MYP1.SGM 18MYP1 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules (f) Compliance Comply with this AD within the compliance times specified, unless already done. (h) Inspections and Checks for Groups 2 and 3 Airplanes For airplanes identified as Groups 2 and 3 in Boeing Alert Service Bulletin 737– 55A1099, Revision 1, dated October 21, 2016: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016, do the applicable inspections and checks of elevator hinge numbers 4 and 6 and related components specified in paragraphs (h)(1) through (h)(8) of this AD, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016, except as required by paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the actions specified in paragraphs (h)(1) through (h)(8) of this AD thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016. (1) For Groups 2 and 3 airplanes: A high frequency eddy current (HFEC) inspection for cracking of the elevator hinge numbers 4 and 6. (2) For Groups 2 and 3 airplanes: A loose bolt check at elevator hinge numbers 4 and 6. (3) For Groups 2 and 3 airplanes: An HFEC inspection and low frequency eddy current (LFEC) inspection for cracking of the horizontal stabilizer forward of elevator hinge numbers 4 and 6. (4) For Groups 2 and 3 airplanes: A loose bolt check of horizontal stabilizer attach plates at elevator hinge numbers 4 and 6. (5) For Groups 2 and 3 airplanes: A detailed inspection of the horizontal stabilizer rear spar outer mold line, gusset plate, and inspar skin for any corrosion. (6) For Group 2, Configuration 2, and Group 3 airplanes: A general visual inspection of the elevator front spar around hinge numbers 4 and 6 for any ply damage. (7) For Group 2 and 3 airplanes: A tap test inspection of the elevator skin for any delamination at elevator hinge numbers 4 and 6. (8) For Group 2, Configuration 2, and Group 3 airplanes on which elevator hinge fitting assembly 65C31307-( ) is installed at elevator hinge number 6: An HFEC inspection of the hinge fitting for any crack. (g) Actions for Group 1 Airplanes For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016: Within 120 days after the effective date of this AD, do inspections and checks of the elevator and horizontal stabilizer at elevator hinge numbers 4 and 6 and the replacement and test of the bearing plate at elevator hinge numbers 4 and 6, as specified in Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016, and do all applicable related investigative and corrective actions, using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (i) Repetitive Bearing Plate Replacement and Test For airplanes identified as Group 2, Configuration 2, and Group 3 in Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1099, Revision 1, 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2017–0473; Directorate Identifier 2016– NM–195–AD. (a) Comments Due Date We must receive comments by July 3, 2017. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. jstallworth on DSK7TPTVN1PROD with PROPOSALS (e) Unsafe Condition This AD was prompted by a report indicating that wear of the bearing plate slider bushings could cause disconnection of elevator hinge number 4 or number 6, which could excite the horizontal stabilizer under certain in-flight speed/altitude conditions and lead to degradation of the structure, departure of the elevator or horizontal stabilizer from the airplane, and loss of continued safe flight and landing. VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 22765 dated October 21, 2016, except as required by paragraph (j)(2) of this AD. All applicable related investigative and corrective actions must be done before further flight. Repeat the actions specified in paragraphs (i)(1) and (i)(2) of this AD thereafter at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016. (1) Replace the bearing plates at elevator hinge numbers 4 and 6. (2) Do an elevator hinge bearing plate binding test at hinge numbers 4 and 6. (j) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016, specifies a compliance time ‘‘after the original issue date of this Service Bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although Boeing Alert Service Bulletin 737–55A1099, Revision 1, dated October 21, 2016, specifies to contact Boeing for repair instructions, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (k) Parts Installation Limitation As of the effective date of this AD: A horizontal stabilizer, an elevator, or a bearing plate may be installed on any airplane, provided the actions required by paragraphs (h) and (i) of this AD are done within the applicable compliance times specified in paragraphs (h) and (i) of this AD. (l) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737–55A1099, dated July 5, 2016. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has E:\FR\FM\18MYP1.SGM 18MYP1 22766 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules jstallworth on DSK7TPTVN1PROD with PROPOSALS been authorized by the Manager, Los Angeles ACO, 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. (4) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(4)(i) and (m)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0474; Directorate Identifier 2016–NM–096–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. (Type Certificate Previously Held by Canadair Limited) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2011–03– 08, for certain Bombardier, Inc., Model CL–215–1A10 (CL–215), CL–215–6B11 (CL–215T Variant), and CL–215–6B11 (CL–415 Variant) airplanes. AD 2011– 03–08 currently requires an inspection to determine the number of flight cycles accumulated by certain accumulators installed on the airplane, and repetitive inspections of the accumulators for (n) Related Information cracks and replacement if necessary. Since we issued AD 2011–03–08, we (1) For more information about this AD, contact Lu Lu, Aerospace Engineer, Airframe determined that a terminating action is Branch, ANM–120S, FAA, Seattle ACO, 1601 necessary to address the identified unsafe condition. This proposed AD Lind Avenue SW., Renton, WA 98057–3356; would add a requirement for the phone: 425–917–6478; fax: 425–917–6590; terminating action. We are proposing email: lu.lu@faa.gov. this AD to address the unsafe condition (2) For information about AMOCs, contact on these products. George Garrido, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los DATES: We must receive comments on Angeles ACO, 3960 Paramount Boulevard, this proposed AD by July 3, 2017. Lakewood, CA 90712–4137; phone: 562–627– ADDRESSES: You may send comments, 5357; fax: 562–627–5210; email: using the procedures found in 14 CFR george.garrido@faa.gov. 11.43 and 11.45, by any of the following (3) For service information identified in methods: this AD, contact Boeing Commercial • Federal eRulemaking Portal: Go to Airplanes, Attention: Contractual & Data http://www.regulations.gov. Follow the Services (C&DS), 2600 Westminster Blvd., instructions for submitting comments. MC 110–SK57, Seal Beach, CA 90740–5600; • Fax: 202–493–2251. telephone 562–797–1717; Internet https:// • Mail: U.S. Department of www.myboeingfleet.com. You may view this Transportation, Docket Operations, M– referenced service information at the FAA, 30, West Building Ground Floor, Room Transport Airplane Directorate, 1601 Lind W12–140, 1200 New Jersey Avenue SE., Avenue SW., Renton, WA. For information Washington, DC 20590. on the availability of this material at the • Hand Delivery: U.S. Department of FAA, call 425–227–1221. Transportation, Docket Operations, M– Issued in Renton, Washington, on May 10, 30, West Building Ground Floor, Room 2017. W12–140, 1200 New Jersey Avenue SE., Jeffrey E. Duven, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Manager, Transport Airplane Directorate, Federal holidays. Aircraft Certification Service. For service information identified in [FR Doc. 2017–10031 Filed 5–17–17; 8:45 am] this NPRM, contact Bombardier, Inc., BILLING CODE 4910–13–P ˆ 400 Cote-Vertu Road West, Dorval, ´ Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You may view this referenced service information VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0474; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–0474; Directorate Identifier 2016–NM–096–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 On January 26, 2011, we issued AD 2011–03–08, Amendment 39–16592 (76 FR 6536, February 7, 2011) (‘‘AD 2011– 03–08’’), for certain Bombardier, Inc., Model CL–215–1A10 (CL–215), CL– 215–6B11 (CL–215T Variant), and CL– 215–6B11 (CL–415 Variant) airplanes. AD 2011–03–08 was prompted by reports of seven cases of on-ground hydraulic accumulator screw cap or end cap failure, which have resulted in loss of the associated hydraulic system and E:\FR\FM\18MYP1.SGM 18MYP1

Agencies

[Federal Register Volume 82, Number 95 (Thursday, May 18, 2017)]
[Proposed Rules]
[Pages 22763-22766]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10031]



[[Page 22763]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0473; Directorate Identifier 2016-NM-195-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 adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This proposed AD was prompted by a report indicating 
that wear of the bearing plate slider bushings could cause 
disconnection of certain elevator hinges, which could excite the 
horizontal stabilizer under certain in-flight speed/altitude conditions 
and lead to degradation of the structure. This proposed AD would 
require repetitive inspections and checks of certain elevator hinges 
and related components, repetitive replacements and tests of the 
bearing plate, and related investigative and corrective actions if 
necessary. We are proposing this AD to address the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by July 3, 2017.

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 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. It is also 
available on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0473.

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-2017-
0473; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Lu Lu, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6478; fax: 
425-917-6590; email: lu.lu@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0473; 
Directorate Identifier 2016-NM-195-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received a report indicating that analysis following a 
special certification review of the horizontal stabilizer determined 
that wear of the bearing plate slider bushings could cause 
disconnection of elevator hinge number 4 or number 6. This 
disconnection could excite the horizontal stabilizer under certain in-
flight speed/altitude conditions and lead to degradation of the 
structure due to tab flutter, hinge wear, spar chord corrosion, hinge 
rib web chafing, hinge rib chord cracking, and inspar lower skin 
cracking. One or more of these conditions, if not corrected, could 
result in heavy airplane vibration and damage, which could lead to 
departure of the elevator and/or horizontal stabilizer from the 
airplane, and loss of continued safe flight and landing.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-55A1099, Revision 1, 
dated October 21, 2016. The service information describes procedures 
for repetitive inspections and checks of elevator hinge numbers 4 and 6 
and related components, repetitive replacements and tests of the 
bearing plate, and related 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 require accomplishing the actions specified 
in the service information identified previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' 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-2017-0473.
    The phrase ``related investigative actions'' is used in this 
proposed AD. Related investigative actions are follow-on actions that 
(1) are related to the primary action, and (2) further investigate the 
nature of any condition found. Related investigative actions in an AD 
could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
Corrective actions correct or address any condition found. Corrective 
actions in an AD could include, for example, repairs.

[[Page 22764]]

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated 
October 21, 2016, specifies to contact the manufacturer for certain 
instructions, but this proposed AD would require using repair methods, 
modification deviations, and alteration deviations in one of the 
following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 192 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Elevator hinge high frequency      15 work-hours x $85              $0  $1,275 per           $244,800 per
 eddy current (HFEC) inspection,    per hour = $1,275                    inspection/check     inspection/check
 loose bolt check.                  per inspection/                      cycle.               cycle.
                                    check cycle.
Horizontal stabilizer HFEC and     13 work-hours x $85               0  $1,105 per           $212,160 per
 low frequency eddy current         per hour = $1,105                    inspection/check     inspection/check
 (LFEC) inspection, loose bolt      per inspection/                      cycle.               cycle.
 check.                             check cycle.
Horizontal stabilizer detailed     5 work-hours x 85                 0  $425 per inspection  $81,600 per
 corrosion inspection.              per hour = 425 per                   cycle.               inspection cycle.
                                    inspection cycle.
Elevator general visual            Up to 4 work-hours                0  Up to $340 per       Up to $65,280 per
 inspection for ply damage.         x 85 per hour =                      inspection cycle.    inspection cycle.
                                    340 per inspection
                                    cycle.
Elevator skin tap test inspection  Up to 6 work-hours                0  Up to $510 per       Up to $97,920 per
 for delamination.                  x 85 per hour =                      inspection cycle.    inspection cycle.
                                    510 per inspection
                                    cycle.
Elevator hinge bearing plate       Up to 20 work-hours           4,860  Up to $6,560 per     Up to $1,259,520
 replacement and binding test.      x 85 per hour =                      replacement/test     per replacement/
                                    1,700 per                            cycle.               test cycle.
                                    replacement/test
                                    cycle.
Elevator hinge fitting HFEC        Up to 5 work-hours                0  Up to $425 per       Up to $81,600 per
 inspection.                        x 85 per hour =                      inspection cycle.    inspection cycle.
                                    425 per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary related 
investigative and corrective actions that would be required based on 
the results of the proposed inspection. We have no way of determining 
the number of aircraft that might need these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Elevator hinge conditional inspections,         28 work-hours x $85 per hour =            \1\ $0          $2,380
 measurements, replacements, and repairs.        $2,380.
Horizontal stabilizer conditional inspections,  28 work-hours x $85 per hour =             \1\ 0           2,380
 replacements, and repairs.                      $2,380.
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide cost estimates for the parts for on-
  condition repairs.

Authority for This Rulemaking

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

Regulatory Findings

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

[[Page 22765]]

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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2017-0473; Directorate Identifier 
2016-NM-195-AD.

(a) Comments Due Date

    We must receive comments by July 3, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by a report indicating that wear of the 
bearing plate slider bushings could cause disconnection of elevator 
hinge number 4 or number 6, which could excite the horizontal 
stabilizer under certain in-flight speed/altitude conditions and 
lead to degradation of the structure, departure of the elevator or 
horizontal stabilizer from the airplane, and loss of continued safe 
flight and landing.

(f) Compliance

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

(g) Actions for Group 1 Airplanes

    For airplanes identified as Group 1 in Boeing Alert Service 
Bulletin 737-55A1099, Revision 1, dated October 21, 2016: Within 120 
days after the effective date of this AD, do inspections and checks 
of the elevator and horizontal stabilizer at elevator hinge numbers 
4 and 6 and the replacement and test of the bearing plate at 
elevator hinge numbers 4 and 6, as specified in Boeing Alert Service 
Bulletin 737-55A1099, Revision 1, dated October 21, 2016, and do all 
applicable related investigative and corrective actions, using a 
method approved in accordance with the procedures specified in 
paragraph (m) of this AD.

(h) Inspections and Checks for Groups 2 and 3 Airplanes

    For airplanes identified as Groups 2 and 3 in Boeing Alert 
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016: 
Except as required by paragraph (j)(1) of this AD, at the applicable 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, do 
the applicable inspections and checks of elevator hinge numbers 4 
and 6 and related components specified in paragraphs (h)(1) through 
(h)(8) of this AD, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1099, Revision 
1, dated October 21, 2016, except as required by paragraph (j)(2) of 
this AD. Do all applicable related investigative and corrective 
actions before further flight. Repeat the actions specified in 
paragraphs (h)(1) through (h)(8) of this AD thereafter at the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 
21, 2016.
    (1) For Groups 2 and 3 airplanes: A high frequency eddy current 
(HFEC) inspection for cracking of the elevator hinge numbers 4 and 
6.
    (2) For Groups 2 and 3 airplanes: A loose bolt check at elevator 
hinge numbers 4 and 6.
    (3) For Groups 2 and 3 airplanes: An HFEC inspection and low 
frequency eddy current (LFEC) inspection for cracking of the 
horizontal stabilizer forward of elevator hinge numbers 4 and 6.
    (4) For Groups 2 and 3 airplanes: A loose bolt check of 
horizontal stabilizer attach plates at elevator hinge numbers 4 and 
6.
    (5) For Groups 2 and 3 airplanes: A detailed inspection of the 
horizontal stabilizer rear spar outer mold line, gusset plate, and 
inspar skin for any corrosion.
    (6) For Group 2, Configuration 2, and Group 3 airplanes: A 
general visual inspection of the elevator front spar around hinge 
numbers 4 and 6 for any ply damage.
    (7) For Group 2 and 3 airplanes: A tap test inspection of the 
elevator skin for any delamination at elevator hinge numbers 4 and 
6.
    (8) For Group 2, Configuration 2, and Group 3 airplanes on which 
elevator hinge fitting assembly 65C31307-( ) is installed at 
elevator hinge number 6: An HFEC inspection of the hinge fitting for 
any crack.

(i) Repetitive Bearing Plate Replacement and Test

    For airplanes identified as Group 2, Configuration 2, and Group 
3 in Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated 
October 21, 2016: Except as required by paragraph (j)(1) of this AD, 
at the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated 
October 21, 2016, do the actions specified in paragraphs (i)(1) and 
(i)(2) of this AD, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1099, Revision 
1, dated October 21, 2016, except as required by paragraph (j)(2) of 
this AD. All applicable related investigative and corrective actions 
must be done before further flight. Repeat the actions specified in 
paragraphs (i)(1) and (i)(2) of this AD thereafter at the applicable 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016.
    (1) Replace the bearing plates at elevator hinge numbers 4 and 
6.
    (2) Do an elevator hinge bearing plate binding test at hinge 
numbers 4 and 6.

(j) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 737-55A1099, Revision 1, 
dated October 21, 2016, specifies a compliance time ``after the 
original issue date of this Service Bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Although Boeing Alert Service Bulletin 737-55A1099, Revision 
1, dated October 21, 2016, specifies to contact Boeing for repair 
instructions, and specifies that action as ``RC'' (Required for 
Compliance), this AD requires repair before further flight using a 
method approved in accordance with the procedures specified in 
paragraph (m) of this AD.

(k) Parts Installation Limitation

    As of the effective date of this AD: A horizontal stabilizer, an 
elevator, or a bearing plate may be installed on any airplane, 
provided the actions required by paragraphs (h) and (i) of this AD 
are done within the applicable compliance times specified in 
paragraphs (h) and (i) of this AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 737-55A1099, dated July 5, 2016.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (n)(2) of this AD. 
Information may be emailed to: 9-ANM-LAACO-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, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has

[[Page 22766]]

been authorized by the Manager, Los Angeles ACO, 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.
    (4) Except as required by paragraph (j)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (m)(4)(i) and 
(m)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(n) Related Information

    (1) For more information about this AD, contact Lu Lu, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; phone: 425-917-6478; fax: 425-
917-6590; email: lu.lu@faa.gov.
    (2) For information about AMOCs, contact George Garrido, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5357; fax: 562-627-5210; email: george.garrido@faa.gov.
    (3) 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 Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on May 10, 2017.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10031 Filed 5-17-17; 8:45 am]
 BILLING CODE 4910-13-P