82 FR 22763 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 95 (May 18, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 95 (May 18, 2017)
| Page Range | 22763-22766 | |
| FR Document | 2017-10031 |
[Federal Register Volume 82, Number 95 (Thursday, May 18, 2017)] [Proposed Rules] [Pages 22763-22766] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10031] [[Page 22763]] ======================================================================= ----------------------------------------------------------------------- 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: [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-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: [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 [[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: [email protected]. (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: [email protected]. (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
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DEPARTMENT OF TRANSPORTATION Renton, WA. For information on the lead to degradation of the structure due
availability of this material at the FAA, to tab flutter, hinge wear, spar chord
Federal Aviation Administration call 425–227–1221. It is also available corrosion, hinge rib web chafing, hinge
on the internet at http:// rib chord cracking, and inspar lower
14 CFR Part 39 www.regulations.gov by searching for skin cracking. One or more of these
[Docket No. FAA–2017–0473; Directorate and locating Docket No. FAA–2017– conditions, if not corrected, could result
Identifier 2016–NM–195–AD] 0473. in heavy airplane vibration and damage,
RIN 2120–AA64 Examining the AD Docket which could lead to departure of the
You may examine the AD docket on elevator and/or horizontal stabilizer
Airworthiness Directives; The Boeing the Internet at http:// from the airplane, and loss of continued
Company Airplanes www.regulations.gov by searching for safe flight and landing.
AGENCY: Federal Aviation and locating Docket No. FAA–2017– Related Service Information Under 1
Administration (FAA), DOT. 0473; or in person at the Docket CFR Part 51
Management Facility between 9 a.m.
ACTION: Notice of proposed rulemaking
and 5 p.m., Monday through Friday, We reviewed Boeing Alert Service
(NPRM). except Federal holidays. The AD docket Bulletin 737–55A1099, Revision 1,
SUMMARY: We propose to adopt a new contains this proposed AD, the dated October 21, 2016. The service
airworthiness directive (AD) for all The regulatory evaluation, any comments information describes procedures for
Boeing Company Model 737–100, –200, received, and other information. The repetitive inspections and checks of
–200C, –300, –400, and –500 series street address for the Docket Office elevator hinge numbers 4 and 6 and
airplanes. This proposed AD was (phone: 800–647–5527) is in the related components, repetitive
prompted by a report indicating that ADDRESSES section. Comments will be replacements and tests of the bearing
wear of the bearing plate slider bushings available in the AD docket shortly after plate, and related investigative and
could cause disconnection of certain receipt. corrective actions. This service
elevator hinges, which could excite the FOR FURTHER INFORMATION CONTACT: Lu information is reasonably available
horizontal stabilizer under certain in- Lu, Aerospace Engineer, Airframe because the interested parties have
flight speed/altitude conditions and Branch, ANM–120S, FAA, Seattle access to it through their normal course
lead to degradation of the structure. Aircraft Certification Office (ACO), 1601 of business or by the means identified
This proposed AD would require Lind Avenue SW., Renton, WA 98057– in the ADDRESSES section.
repetitive inspections and checks of 3356; phone: 425–917–6478; fax: 425–
certain elevator hinges and related 917–6590; email: lu.lu@faa.gov. FAA’s Determination
components, repetitive replacements SUPPLEMENTARY INFORMATION:
We are proposing this AD because we
and tests of the bearing plate, and Comments Invited evaluated all the relevant information
related investigative and corrective
We invite you to send any written and determined the unsafe condition
actions if necessary. We are proposing
this AD to address the unsafe condition relevant data, views, or arguments about described previously is likely to exist or
on these products. this proposal. Send your comments to develop in other products of the same
an address listed under the ADDRESSES type design.
DATES: We must receive comments on
section. Include ‘‘Docket No. FAA–
this proposed AD by July 3, 2017. 2017–0473; Directorate Identifier 2016– Proposed AD Requirements
ADDRESSES: You may send comments, NM–195–AD’’ at the beginning of your
using the procedures found in 14 CFR This proposed AD would require
comments. We specifically invite accomplishing the actions specified in
11.43 and 11.45, by any of the following comments on the overall regulatory,
methods: the service information identified
economic, environmental, and energy
• Federal eRulemaking Portal: Go to previously, except as discussed under
aspects of this proposed AD. We will
http://www.regulations.gov. Follow the ‘‘Differences Between this Proposed AD
consider all comments received by the
instructions for submitting comments. and the Service Information.’’ For
closing date and may amend this
• Fax: 202–493–2251. proposed AD because of those information on the procedures and
• Mail: U.S. Department of comments. compliance times, see this service
Transportation, Docket Operations, M– We will post all comments we information at http://
30, West Building Ground Floor, Room receive, without change, to http:// www.regulations.gov by searching for
W12–140, 1200 New Jersey Avenue SE., www.regulations.gov, including any and locating Docket No. FAA–2017–
Washington, DC 20590. personal information you provide. We 0473.
• Hand Delivery: Deliver to Mail will also post a report summarizing each The phrase ‘‘related investigative
address above between 9 a.m. and 5 substantive verbal contact we receive actions’’ is used in this proposed AD.
p.m., Monday through Friday, except about this proposed AD. Related investigative actions are follow-
Federal holidays. on actions that (1) are related to the
For service information identified in Discussion
primary action, and (2) further
this NPRM, contact Boeing Commercial We have received a report indicating
investigate the nature of any condition
Airplanes, Attention: Contractual & Data that analysis following a special
jstallworth on DSK7TPTVN1PROD with PROPOSALS
found. Related investigative actions in
Services (C&DS), 2600 Westminster certification review of the horizontal
an AD could include, for example,
Blvd., MC 110–SK57, Seal Beach, CA stabilizer determined that wear of the
90740–5600; telephone 562–797–1717; bearing plate slider bushings could inspections.
Internet https:// cause disconnection of elevator hinge The phrase ‘‘corrective actions’’ is
www.myboeingfleet.com. You may view number 4 or number 6. This used in this proposed AD. Corrective
this referenced service information at disconnection could excite the actions correct or address any condition
the FAA, Transport Airplane horizontal stabilizer under certain in- found. Corrective actions in an AD
Directorate, 1601 Lind Avenue SW., flight speed/altitude conditions and could include, for example, repairs.
VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\18MYP1.SGM 18MYP1](https://thefederalregister.org/doc/82_FR_22858/page/1.svg)
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List of Subjects in 14 CFR Part 39 (h) Inspections and Checks for Groups 2 and dated October 21, 2016, except as required by
3 Airplanes paragraph (j)(2) of this AD. All applicable
Air transportation, Aircraft, Aviation related investigative and corrective actions
safety, Incorporation by reference, For airplanes identified as Groups 2 and 3
in Boeing Alert Service Bulletin 737– must be done before further flight. Repeat the
Safety. 55A1099, Revision 1, dated October 21, 2016: actions specified in paragraphs (i)(1) and
Except as required by paragraph (j)(1) of this (i)(2) of this AD thereafter at the applicable
The Proposed Amendment time specified in paragraph 1.E.,
AD, at the applicable time specified in
Accordingly, under the authority paragraph 1.E., ‘‘Compliance,’’ of Boeing ‘‘Compliance,’’ of Boeing Alert Service
delegated to me by the Administrator, Alert Service Bulletin 737–55A1099, Bulletin 737–55A1099, Revision 1, dated
the FAA proposes to amend 14 CFR part Revision 1, dated October 21, 2016, do the October 21, 2016.
39 as follows: applicable inspections and checks of elevator (1) Replace the bearing plates at elevator
hinge numbers 4 and 6 and related hinge numbers 4 and 6.
PART 39—AIRWORTHINESS components specified in paragraphs (h)(1) (2) Do an elevator hinge bearing plate
through (h)(8) of this AD, and do all binding test at hinge numbers 4 and 6.
DIRECTIVES
applicable related investigative and (j) Exceptions to Service Information
■ 1. The authority citation for part 39 corrective actions, in accordance with the Specifications
continues to read as follows: Accomplishment Instructions of Boeing Alert
(1) Where Boeing Alert Service Bulletin
Service Bulletin 737–55A1099, Revision 1,
Authority: 49 U.S.C. 106(g), 40113, 44701. 737–55A1099, Revision 1, dated October 21,
dated October 21, 2016, except as required by
2016, specifies a compliance time ‘‘after the
§ 39.13 [Amended] paragraph (j)(2) of this AD. Do all applicable
original issue date of this Service Bulletin,’’
related investigative and corrective actions
■ 2. The FAA amends § 39.13 by adding this AD requires compliance within the
before further flight. Repeat the actions
the following new airworthiness specified compliance time after the effective
specified in paragraphs (h)(1) through (h)(8)
directive (AD): date of this AD.
of this AD thereafter at the applicable times
(2) Although Boeing Alert Service Bulletin
The Boeing Company: Docket No. FAA– specified in paragraph 1.E., ‘‘Compliance,’’ of
737–55A1099, Revision 1, dated October 21,
2017–0473; Directorate Identifier 2016– Boeing Alert Service Bulletin 737–55A1099,
2016, specifies to contact Boeing for repair
NM–195–AD. Revision 1, dated October 21, 2016.
instructions, and specifies that action as
(1) For Groups 2 and 3 airplanes: A high
(a) Comments Due Date ‘‘RC’’ (Required for Compliance), this AD
frequency eddy current (HFEC) inspection for
requires repair before further flight using a
We must receive comments by July 3, 2017. cracking of the elevator hinge numbers 4 and
method approved in accordance with the
6.
(b) Affected ADs procedures specified in paragraph (m) of this
(2) For Groups 2 and 3 airplanes: A loose
AD.
None. bolt check at elevator hinge numbers 4 and
6. (k) Parts Installation Limitation
(c) Applicability (3) For Groups 2 and 3 airplanes: An HFEC As of the effective date of this AD: A
This AD applies to all The Boeing inspection and low frequency eddy current horizontal stabilizer, an elevator, or a bearing
Company Model 737–100, –200, –200C, (LFEC) inspection for cracking of the plate may be installed on any airplane,
–300, –400, and –500 series airplanes, horizontal stabilizer forward of elevator provided the actions required by paragraphs
certificated in any category. hinge numbers 4 and 6. (h) and (i) of this AD are done within the
(4) For Groups 2 and 3 airplanes: A loose applicable compliance times specified in
(d) Subject
bolt check of horizontal stabilizer attach paragraphs (h) and (i) of this AD.
Air Transport Association (ATA) of plates at elevator hinge numbers 4 and 6.
America Code 55, Stabilizers. (5) For Groups 2 and 3 airplanes: A (l) Credit for Previous Actions
(e) Unsafe Condition detailed inspection of the horizontal This paragraph provides credit for the
stabilizer rear spar outer mold line, gusset actions specified in paragraphs (h) and (i) of
This AD was prompted by a report plate, and inspar skin for any corrosion.
indicating that wear of the bearing plate this AD, if those actions were performed
(6) For Group 2, Configuration 2, and before the effective date of this AD using
slider bushings could cause disconnection of Group 3 airplanes: A general visual
elevator hinge number 4 or number 6, which Boeing Alert Service Bulletin 737–55A1099,
inspection of the elevator front spar around dated July 5, 2016.
could excite the horizontal stabilizer under hinge numbers 4 and 6 for any ply damage.
certain in-flight speed/altitude conditions (m) Alternative Methods of Compliance
(7) For Group 2 and 3 airplanes: A tap test
and lead to degradation of the structure, (AMOCs)
inspection of the elevator skin for any
departure of the elevator or horizontal
delamination at elevator hinge numbers 4 (1) The Manager, Los Angeles Aircraft
stabilizer from the airplane, and loss of
and 6. Certification Office (ACO), FAA, has the
continued safe flight and landing.
(8) For Group 2, Configuration 2, and authority to approve AMOCs for this AD, if
(f) Compliance Group 3 airplanes on which elevator hinge requested using the procedures found in 14
Comply with this AD within the fitting assembly 65C31307-( ) is installed at CFR 39.19. In accordance with 14 CFR 39.19,
compliance times specified, unless already elevator hinge number 6: An HFEC send your request to your principal inspector
done. inspection of the hinge fitting for any crack. or local Flight Standards District Office, as
appropriate. If sending information directly
(g) Actions for Group 1 Airplanes (i) Repetitive Bearing Plate Replacement and
to the manager of the ACO, send it to the
Test
For airplanes identified as Group 1 in attention of the person identified in
Boeing Alert Service Bulletin 737–55A1099, For airplanes identified as Group 2, paragraph (n)(2) of this AD. Information may
Revision 1, dated October 21, 2016: Within Configuration 2, and Group 3 in Boeing Alert be emailed to: 9-ANM-LAACO-AMOC-
120 days after the effective date of this AD, Service Bulletin 737–55A1099, Revision 1, Requests@faa.gov.
do inspections and checks of the elevator and dated October 21, 2016: Except as required (2) Before using any approved AMOC,
horizontal stabilizer at elevator hinge by paragraph (j)(1) of this AD, at the notify your appropriate principal inspector,
jstallworth on DSK7TPTVN1PROD with PROPOSALS
numbers 4 and 6 and the replacement and applicable time specified in paragraph 1.E., or lacking a principal inspector, the manager
test of the bearing plate at elevator hinge ‘‘Compliance,’’ of Boeing Alert Service of the local flight standards district office/
numbers 4 and 6, as specified in Boeing Alert Bulletin 737–55A1099, Revision 1, dated certificate holding district office.
Service Bulletin 737–55A1099, Revision 1, October 21, 2016, do the actions specified in (3) An AMOC that provides an acceptable
dated October 21, 2016, and do all applicable paragraphs (i)(1) and (i)(2) of this AD, and do level of safety may be used for any repair,
related investigative and corrective actions, all applicable related investigative and modification, or alteration required by this
using a method approved in accordance with corrective actions, in accordance with the AD if it is approved by the Boeing
the procedures specified in paragraph (m) of Accomplishment Instructions of Boeing Alert Commercial Airplanes Organization
this AD. Service Bulletin 737–55A1099, Revision 1, Designation Authorization (ODA) that has
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![22766 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules
been authorized by the Manager, Los Angeles DEPARTMENT OF TRANSPORTATION at the FAA, Transport Airplane
ACO, to make those findings. To be Directorate, 1601 Lind Avenue SW.,
approved, the repair method, modification Federal Aviation Administration Renton, WA. For information on the
deviation, or alteration deviation must meet availability of this material at the FAA,
the certification basis of the airplane, and the 14 CFR Part 39 call 425–227–1221.
approval must specifically refer to this AD.
[Docket No. FAA–2017–0474; Directorate Examining the AD Docket
(4) Except as required by paragraph (j)(2)
Identifier 2016–NM–096–AD]
of this AD: For service information that You may examine the AD docket on
contains steps that are labeled as Required RIN 2120–AA64 the Internet at http://
for Compliance (RC), the provisions of www.regulations.gov by searching for
paragraphs (m)(4)(i) and (m)(4)(ii) of this AD Airworthiness Directives; Bombardier, and locating Docket No. FAA–2017–
apply. Inc. (Type Certificate Previously Held 0474; or in person at the Docket
(i) The steps labeled as RC, including by Canadair Limited) Airplanes Management Facility between 9 a.m.
substeps under an RC step and any figures
AGENCY: Federal Aviation and 5 p.m., Monday through Friday,
identified in an RC step, must be done to
Administration (FAA), DOT. except Federal holidays. The AD docket
comply with the AD. If a step or substep is contains this proposed AD, the
labeled ‘‘RC Exempt,’’ then the RC ACTION: Notice of proposed rulemaking
regulatory evaluation, any comments
requirement is removed from that step or (NPRM). received, and other information. The
substep. An AMOC is required for any We propose to supersede
SUMMARY: street address for the Docket Operations
deviations to RC steps, including substeps office (telephone 800–647–5527) is in
Airworthiness Directive (AD) 2011–03–
and identified figures. the ADDRESSES section. Comments will
08, for certain Bombardier, Inc., Model
(ii) Steps not labeled as RC may be be available in the AD docket shortly
CL–215–1A10 (CL–215), CL–215–6B11
deviated from using accepted methods in after receipt.
(CL–215T Variant), and CL–215–6B11
accordance with the operator’s maintenance FOR FURTHER INFORMATION CONTACT:
(CL–415 Variant) airplanes. AD 2011–
or inspection program without obtaining Cesar A. Gomez, Aerospace Engineer,
03–08 currently requires an inspection
approval of an AMOC, provided the RC steps, Airframe and Mechanical Systems
to determine the number of flight cycles
including substeps and identified figures, can
accumulated by certain accumulators Branch, ANE–171, FAA, New York
still be done as specified, and the airplane Aircraft Certification Office (ACO), 1600
can be put back in an airworthy condition.
installed on the airplane, and repetitive
inspections of the accumulators for Stewart Avenue, Suite 410, Westbury,
(n) Related Information cracks and replacement if necessary. NY 11590; telephone 516–228–7318; fax
(1) For more information about this AD, Since we issued AD 2011–03–08, we 516–794–5531.
contact Lu Lu, Aerospace Engineer, Airframe determined that a terminating action is SUPPLEMENTARY INFORMATION:
Branch, ANM–120S, FAA, Seattle ACO, 1601 necessary to address the identified Comments Invited
Lind Avenue SW., Renton, WA 98057–3356; unsafe condition. This proposed AD
phone: 425–917–6478; fax: 425–917–6590; would add a requirement for the We invite you to send any written
email: lu.lu@faa.gov. terminating action. We are proposing relevant data, views, or arguments about
(2) For information about AMOCs, contact this AD to address the unsafe condition this proposed AD. Send your comments
George Garrido, Aerospace Engineer, on these products. to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
Airframe Branch, ANM–120L, FAA, Los DATES: We must receive comments on
Angeles ACO, 3960 Paramount Boulevard, FAA–2017–0474; Directorate Identifier
this proposed AD by July 3, 2017. 2016–NM–096–AD’’ at the beginning of
Lakewood, CA 90712–4137; phone: 562–627– ADDRESSES: You may send comments,
5357; fax: 562–627–5210; email: your comments. We specifically invite
using the procedures found in 14 CFR comments on the overall regulatory,
george.garrido@faa.gov.
11.43 and 11.45, by any of the following economic, environmental, and energy
(3) For service information identified in
methods: aspects of this proposed AD. We will
this AD, contact Boeing Commercial
• Federal eRulemaking Portal: Go to consider all comments received by the
Airplanes, Attention: Contractual & Data
http://www.regulations.gov. Follow the closing date and may amend this
Services (C&DS), 2600 Westminster Blvd.,
instructions for submitting comments. proposed AD based on those comments.
MC 110–SK57, Seal Beach, CA 90740–5600;
• Fax: 202–493–2251. We will post all comments we
telephone 562–797–1717; Internet https://
• Mail: U.S. Department of receive, without change, to http://
www.myboeingfleet.com. You may view this
Transportation, Docket Operations, M– www.regulations.gov, including any
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
30, West Building Ground Floor, Room personal information you provide. We
Avenue SW., Renton, WA. For information
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
on the availability of this material at the
Washington, DC 20590. substantive verbal contact we receive
FAA, call 425–227–1221.
• Hand Delivery: U.S. Department of about this proposed AD.
Transportation, Docket Operations, M–
Issued in Renton, Washington, on May 10, 30, West Building Ground Floor, Room Discussion
2017. W12–140, 1200 New Jersey Avenue SE., On January 26, 2011, we issued AD
Jeffrey E. Duven, Washington, DC, between 9 a.m. and 5 2011–03–08, Amendment 39–16592 (76
Manager, Transport Airplane Directorate, p.m., Monday through Friday, except FR 6536, February 7, 2011) (‘‘AD 2011–
Aircraft Certification Service. Federal holidays. 03–08’’), for certain Bombardier, Inc.,
jstallworth on DSK7TPTVN1PROD with PROPOSALS
[FR Doc. 2017–10031 Filed 5–17–17; 8:45 am] For service information identified in Model CL–215–1A10 (CL–215), CL–
BILLING CODE 4910–13–P
this NPRM, contact Bombardier, Inc., 215–6B11 (CL–215T Variant), and CL–
400 Côte-Vertu Road West, Dorval, 215–6B11 (CL–415 Variant) airplanes.
Québec H4S 1Y9, Canada; telephone AD 2011–03–08 was prompted by
514–855–5000; fax 514–855–7401; email reports of seven cases of on-ground
thd.crj@aero.bombardier.com; Internet hydraulic accumulator screw cap or end
http://www.bombardier.com. You may cap failure, which have resulted in loss
view this referenced service information of the associated hydraulic system and
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Document Created: 2017-05-18 01:20:43
Document Modified: 2017-05-18 01:20:43
| 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 July 3, 2017. | |
| 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: [email protected] | |
| FR Citation | 82 FR 22763 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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