82 FR 58709 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 239 (December 14, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 239 (December 14, 2017)
| Page Range | 58709-58713 | |
| FR Document | 2017-26619 |
[Federal Register Volume 82, Number 239 (Thursday, December 14, 2017)] [Rules and Regulations] [Pages 58709-58713] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-26619] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0473; Product Identifier 2016-NM-195-AD; Amendment 39-19124; AD 2017-25-10] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This 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 AD requires 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 issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 18, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 18, 2018. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 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 final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5357; fax: 562-627- 5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM published in the Federal Register on May 18, 2017 (82 FR 22763). The NPRM was prompted by 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. The NPRM proposed to require 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 if necessary. We are issuing this AD to detect and correct wear of the bearing plate slider bushings, which could result in heavy airplane vibration and damage and could lead to departure of the elevator and/or horizontal stabilizer from the airplane, and loss of continued safe flight and landing. [[Page 58710]] Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM Air Line Pilots Association, International (ALPA) concurred with the content of the NPRM. Request To Change Paragraph (g) of This AD Boeing stated that no inspections are specified in Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, for Group 1 airplanes and requested that the reference to Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, be removed from paragraph (g) of this AD. The European Aviation Safety Agency (EASA) observed that in paragraph (g) of the proposed AD, the reference to Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, for Group 1 airplanes, is not consistent with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, which states only that Group 1 airplanes have exceeded their limit of validity (LOV) and gives no further advice. We agree with the commenters. We have removed the reference to Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, from the compliance requirements specified in paragraph (g) of this AD. Request To Extend Inspections and Checks to All Hinges EASA suggested that the inspections and checks in the proposed AD be extended to all hinges because any other loose hinge could create overloading in adjacent hinges, and therefore could contribute to the failure of hinges 4 and 6. We do not agree with the commenter's assessment. We have consulted with Boeing and confirmed the following information. Hinge fittings 1 and 2 support thrust loads only and do not have the sliding bearing plates. Therefore, these fittings do not need inspections to address the unsafe condition. Boeing's flutter analysis shows that failure (disconnect) at either hinge 4 or 6 is flutter critical. However, a failed hinge 3 or 5, with the shorter span between adjacent hinges, will have less weight relative to stiffness, such that instability does not occur. The fatigue loads on the affected Model 737 airplane elevator are not substantial. If hinge 3 or 5 becomes loose, the load increase on hinge 4 or 6 is insignificant. If hinge 3 or 5 fails, the inspection and replacement program in Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, will still detect any crack at hinge 4 or 6 before it becomes critical. In addition, the normal maintenance procedure of hinge lubrication per the Maintenance Planning Document during a C check should detect a failed hinge 3 or 5. We have not changed this AD in this regard. Request for Clarification of Group 2, Configuration 1 Instructions EASA requested clarification of the reason that paragraph (i) of the proposed AD includes no repeat instruction for Group 2, Configuration 1 airplanes, regarding bearing plate replacement. Group 2, Configuration 1 airplanes are not included in paragraph (i) of this AD, which contains requirements for repetitive bearing plate replacements and tests, because these airplanes do not have the bearing plates. We have not changed this AD regarding this issue. Request for Confirmation of Sufficient Access EASA requested confirmation that sufficient access exists to adequately inspect and test all areas via the methods defined. Boeing has confirmed that sufficient access exists. Additionally, Boeing has released 737-55A1099 Information Notice 01, dated May 23, 2017, to notify operators that hinge 4 inspections cannot be accomplished if existing repairs are installed in accordance with Boeing Special Attention Service Bulletin 737-55-1059, Revision 1, dated April 6, 2016. In that case, alternative inspection procedures must be approved in accordance with the procedures specified in paragraph (m) of this AD. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. 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. Costs of Compliance We estimate that this AD affects 192 airplanes of U.S. registry. We estimate the following costs to comply with this AD: [[Page 58711]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Elevator hinge high frequency 15 work-hours x $85 per $0 $1,275 per $244,800 per eddy current (HFEC) hour = $1,275 per inspection/check inspection/check inspection, loose bolt check. inspection/check cycle. cycle. cycle. Horizontal stabilizer HFEC and 13 work-hours x $85 per 0 $1,105 per $212,160 per low frequency eddy current hour = $1,105 per inspection/check inspection/check (LFEC) inspection, loose bolt inspection/check cycle. cycle. cycle. check. Horizontal stabilizer detailed 5 work-hours x $85 per 0 $425 per $81,600 per corrosion inspection. hour = $425 per inspection cycle. inspection cycle. inspection cycle. Elevator general visual Up to 4 work-hours x 0 Up to $340 per Up to $65,280 per inspection for ply damage. $85 per hour = $340 inspection cycle. inspection cycle. per inspection cycle. Elevator skin tap test Up to 6 work-hours x 0 Up to $510 per Up to $97,920 per inspection for delamination. $85 per hour = $510 inspection cycle. inspection cycle. per inspection cycle. Elevator hinge bearing plate Up to 20 work-hours x 4,860 Up to $6,560 per Up to $1,259,520 replacement and binding test. $85 per hour = $1,700 replacement/test per replacement/ per replacement/test cycle. test cycle. cycle. Elevator hinge fitting HFEC Up to 5 work-hours x 0 Up to $425 per Up to $81,600 per inspection. $85 per hour = $425 inspection cycle. inspection cycle. 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 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2017-25-10 The Boeing Company: Amendment 39-19124; Docket No. FAA- 2017-0473; Product Identifier 2016-NM-195-AD. (a) Effective Date This AD is effective January 18, 2018. [[Page 58712]] (b) Affected ADs None. (c) Applicability (1) This AD applies to all The Boeing Company Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject 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, 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 elevator 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 ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (n) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (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 [[Page 58713]] 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 For more information about this AD, contact George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5357; fax: 562-627-5210; email: [email protected]. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016. (ii) Reserved. (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. (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on December 4, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-26619 Filed 12-13-17; 8:45 am] BILLING CODE 4910-13-P
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(2) Model F28 Mark 0100 airplanes Issued in Renton, Washington, on Examining the AD Docket
equipped with Rolls-Royce Deutschland December 6, 2017.
TAY–620–15 engines. Dionne Palermo, You may examine the AD docket on
Acting Director, System Oversight Division, the internet at http://
(d) Subject www.regulations.gov by searching for
Aircraft Certification Service.
Air Transport Association (ATA) of [FR Doc. 2017–26833 Filed 12–13–17; 8:45 am] and locating Docket No. FAA–2017–
America Code 76, Engine controls. 0473; or in person at the Docket
BILLING CODE 4910–13–P
(e) Reason Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
This AD was prompted by a report of an
DEPARTMENT OF TRANSPORTATION except Federal holidays. The AD docket
engine multiple fan blade-off (MFBO) event,
contains this final rule, the regulatory
caused by engine fan flutter. We are issuing Federal Aviation Administration evaluation, any comments received, and
this AD to prevent engine MFBO events,
other information. The address for the
which could lead to structural damage and
14 CFR Part 39 Docket Office (phone: 800–647–5527) is
possible reduced controllability of the
airplane. [Docket No. FAA–2017–0473; Product Docket Management Facility, U.S.
Identifier 2016–NM–195–AD; Amendment Department of Transportation, Docket
(f) Compliance 39–19124; AD 2017–25–10] Operations, M–30, West Building
Comply with this AD within the Ground Floor, Room W12–140, 1200
RIN 2120–AA64
compliance times specified, unless already New Jersey Avenue SE, Washington, DC
done. Airworthiness Directives; The Boeing 20590.
(g) Required Action(s) Company Airplanes FOR FURTHER INFORMATION CONTACT:
Within 30 days after the effective date of AGENCY: Federal Aviation George Garrido, Aerospace Engineer,
this AD, request instructions from the Administration (FAA), DOT. Airframe Section, FAA, Los Angeles
Manager, International Section, Transport ACTION: Final rule.
ACO Branch, 3960 Paramount
Standards Branch, FAA, to address the Boulevard, Lakewood, CA 90712–4137;
unsafe condition specified in paragraph (e) of SUMMARY: We are adopting a new phone: 562–627–5357; fax: 562–627–
this AD; and accomplish the action(s) at the airworthiness directive (AD) for all The 5210; email: george.garrido@faa.gov.
times specified in, and in accordance with, Boeing Company Model 737–100, –200,
SUPPLEMENTARY INFORMATION:
those instructions. Guidance can be found in –200C, –300, –400, and –500 series
Mandatory Continuing Airworthiness airplanes. This AD was prompted by a Discussion
Information (MCAI) European Aviation report indicating that wear of the
Safety Agency (EASA) AD 2014–0055, dated bearing plate slider bushings could We issued a notice of proposed
March 7, 2014. cause disconnection of certain elevator rulemaking (NPRM) to amend 14 CFR
hinges, which could excite the part 39 by adding an AD that would
(h) Alternative Methods of Compliance apply to all The Boeing Company Model
(AMOCs) horizontal stabilizer under certain in-
flight speed/altitude conditions and 737–100, –200, –200C, –300, –400, and
The Manager, International Section, lead to degradation of the structure. –500 series airplanes. The NPRM
Transport Standards Branch, FAA, has the This AD requires repetitive inspections published in the Federal Register on
authority to approve AMOCs for this AD, if and checks of certain elevator hinges May 18, 2017 (82 FR 22763). The NPRM
requested using the procedures found in 14 was prompted by a report indicating
and related components, repetitive
CFR 39.19. In accordance with 14 CFR 39.19, that analysis following a special
replacements and tests of the bearing
send your request to your principal inspector certification review of the horizontal
plate, and related investigative and
or local Flight Standards District Office, as stabilizer determined that wear of the
corrective actions, if necessary. We are
appropriate. If sending information directly bearing plate slider bushings could
to the International Section, send it to the
issuing this AD to address the unsafe
condition on these products. cause disconnection of elevator hinge
attention of the person identified in
DATES: This AD is effective January 18, number 4 or number 6. This
paragraph (i)(2) of this AD. Information may
2018. disconnection could excite the
be emailed to: 9-ANM-116-AMOC-
REQUESTS@faa.gov. Before using any The Director of the Federal Register horizontal stabilizer under certain in-
approved AMOC, notify your appropriate approved the incorporation by reference flight speed/altitude conditions and
principal inspector, or lacking a principal of a certain publication listed in this AD lead to degradation of the structure due
inspector, the manager of the local flight as of January 18, 2018. to tab flutter, hinge wear, spar chord
standards district office/certificate holding ADDRESSES: For service information corrosion, hinge rib web chafing, hinge
district office. identified in this final rule, contact rib chord cracking, and inspar lower
Boeing Commercial Airplanes, skin cracking. The NPRM proposed to
(i) Related Information require repetitive inspections and
Attention: Contractual & Data Services
(1) Refer to MCAI EASA AD 2014–0055, (C&DS), 2600 Westminster Blvd., MC checks of elevator hinge numbers 4 and
dated March 7, 2014, for related information. 110–SK57, Seal Beach, CA 90740–5600; 6 and related components, repetitive
You may examine the MCAI on the internet replacements and tests of the bearing
telephone 562–797–1717; internet
at http://www.regulations.gov by searching plate, and related investigative and
https://www.myboeingfleet.com. You
for and locating Docket No. FAA–2017–1103. corrective actions if necessary.
may view this service information at the
(2) For more information about this AD,
contact Tom Rodriguez, Aerospace Engineer,
FAA, Transport Standards Branch, 1601 We are issuing this AD to detect and
sradovich on DSK3GMQ082PROD with RULES
International Section, Transport Standards Lind Avenue SW, Renton, WA. For correct wear of the bearing plate slider
Branch, FAA, 1601 Lind Avenue SW, information on the availability of this bushings, which could result in heavy
Renton, WA 98057–3356; telephone: 425– material at the FAA, call 425–227–1221. airplane vibration and damage and
227–1137; fax: 425–227–1149. It is also available on the internet at could lead to departure of the elevator
http://www.regulations.gov by searching and/or horizontal stabilizer from the
(j) Material Incorporated by Reference for and locating Docket No. FAA–2017– airplane, and loss of continued safe
None. 0473. flight and landing.
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ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Elevator hinge high frequency eddy cur- 15 work-hours × $85 per hour = $1,275 $0 $1,275 per inspec- $244,800 per in-
rent (HFEC) inspection, loose bolt per inspection/check cycle. tion/check cycle. spection/check
check. cycle.
Horizontal stabilizer HFEC and low fre- 13 work-hours × $85 per hour = $1,105 0 $1,105 per inspec- $212,160 per in-
quency eddy current (LFEC) inspec- per inspection/check cycle. tion/check cycle. spection/check
tion, loose bolt check. cycle.
Horizontal stabilizer detailed corrosion 5 work-hours × $85 per hour = $425 0 $425 per inspection $81,600 per inspec-
inspection. per inspection cycle. cycle. tion cycle.
Elevator general visual inspection for Up to 4 work-hours × $85 per hour = 0 Up to $340 per in- Up to $65,280 per
ply damage. $340 per inspection cycle. spection cycle. inspection cycle.
Elevator skin tap test inspection for Up to 6 work-hours × $85 per hour = 0 Up to $510 per in- Up to $97,920 per
delamination. $510 per inspection cycle. spection cycle. inspection cycle.
Elevator hinge bearing plate replace- Up to 20 work-hours × $85 per hour = 4,860 Up to $6,560 per Up to $1,259,520
ment and binding test. $1,700 per replacement/test cycle. replacement/test per replacement/
cycle. test cycle.
Elevator hinge fitting HFEC inspection .. Up to 5 work-hours × $85 per hour = 0 Up to $425 per in- Up to $81,600 per
$425 per inspection cycle. spection cycle. inspection cycle.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary related investigative and inspection. We have no way of might need these actions:
corrective actions that would be
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Elevator hinge conditional inspections, measure- 28 work-hours × $85 per hour = $2,380 ...................... 1 $0 $2,380
ments, replacements, and repairs.
Horizontal stabilizer conditional inspections, replace- 28 work-hours × $85 per hour = $2,380 ...................... 1 $0 2,380
ments, and repairs.
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 Compliance and Airworthiness under the criteria of the Regulatory
Division, but during this transition Flexibility Act.
Title 49 of the United States Code period, the Executive Director has
specifies the FAA’s authority to issue List of Subjects in 14 CFR Part 39
delegated the authority to issue ADs
rules on aviation safety. Subtitle I, applicable to transport category Air transportation, Aircraft, Aviation
section 106, describes the authority of airplanes to the Director of the System safety, Incorporation by reference,
the FAA Administrator. Subtitle VII: Oversight Division. Safety.
Aviation Programs, describes in more
detail the scope of the Agency’s Regulatory Findings Adoption of the Amendment
authority. Accordingly, under the authority
This AD will not have federalism
We are issuing this rulemaking under delegated to me by the Administrator,
implications under Executive Order
the authority described in Subtitle VII, the FAA amends 14 CFR part 39 as
13132. This AD will not have a
Part A, Subpart III, Section 44701: follows:
substantial direct effect on the States, on
‘‘General requirements.’’ Under that the relationship between the national
section, Congress charges the FAA with PART 39—AIRWORTHINESS
government and the States, or on the DIRECTIVES
promoting safe flight of civil aircraft in distribution of power and
air commerce by prescribing regulations responsibilities among the various ■ 1. The authority citation for part 39
for practices, methods, and procedures levels of government. continues to read as follows:
the Administrator finds necessary for
For the reasons discussed above, I Authority: 49 U.S.C. 106(g), 40113, 44701.
safety in air commerce. This regulation
certify that this AD:
is within the scope of that authority § 39.13 [Amended]
because it addresses an unsafe condition (1) Is not a ‘‘significant regulatory
that is likely to exist or develop on action’’ under Executive Order 12866, ■ 2. The FAA amends § 39.13 by adding
products identified in this rulemaking (2) Is not a ‘‘significant rule’’ under the following new airworthiness
directive (AD):
sradovich on DSK3GMQ082PROD with RULES
action. DOT Regulatory Policies and Procedures
This AD is issued in accordance with (44 FR 11034, February 26, 1979), 2017–25–10 The Boeing Company:
authority delegated by the Executive (3) Will not affect intrastate aviation Amendment 39–19124; Docket No.
in Alaska, and FAA–2017–0473; Product Identifier
Director, Aircraft Certification Service, 2016–NM–195–AD.
as authorized by FAA Order 8000.51C. (4) Will not have a significant
In accordance with that order, issuance economic impact, positive or negative, (a) Effective Date
of ADs is normally a function of the on a substantial number of small entities This AD is effective January 18, 2018.
VerDate Sep<11>2014 15:57 Dec 13, 2017 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\14DER1.SGM 14DER1](https://thefederalregister.org/doc/82_FR_58948/page/3.svg)
![Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Rules and Regulations 58713
deviations to RC steps, including substeps DEPARTMENT OF TRANSPORTATION FOR FURTHER INFORMATION CONTACT: Jim
and identified figures. Rutherford, Aerospace Engineer, FAA,
(ii) Steps not labeled as RC may be Federal Aviation Administration Small Airplane Standards Branch, 901
deviated from using accepted methods in Locust, Room 301, Kansas City,
accordance with the operator’s maintenance 14 CFR Part 39 Missouri 64106; telephone: (816) 329–
or inspection program without obtaining 4165; fax: (816) 329–4090; email:
[Docket No. FAA–2017–0911; Product
approval of an AMOC, provided the RC steps, jim.rutherford@faa.gov.
Identifier 2017–CE–025–AD; Amendment
including substeps and identified figures, can 39–19121; AD 2017–25–07]
still be done as specified, and the airplane SUPPLEMENTARY INFORMATION:
can be put back in an airworthy condition. RIN 2120–AA64 Discussion
(n) Related Information Airworthiness Directives; Alexander We issued a notice of proposed
For more information about this AD, Schleicher GmbH & Co. rulemaking (NPRM) to amend 14 CFR
contact George Garrido, Aerospace Engineer, Segelflugzeugbau Gliders part 39 by adding an AD that would
Airframe Section, FAA, Los Angeles ACO apply to all Alexander Schleicher GmbH
AGENCY: Federal Aviation
Branch, 3960 Paramount Boulevard, & Co. Segelflugzeugbau Models ASH
Lakewood, CA 90712–4137; phone: 562–627–
Administration (FAA), Department of
25M and ASH 26E gliders. The NPRM
5357; fax: 562–627–5210; email:
Transportation (DOT).
was published in the Federal Register
george.garrido@faa.gov. ACTION: Final rule. on September 22, 2017 (82 FR 44361).
(o) Material Incorporated by Reference SUMMARY: We are adopting a new The NPRM proposed to correct an
airworthiness directive (AD) for all unsafe condition for the specified
(1) The Director of the Federal Register products and was based on mandatory
approved the incorporation by reference Alexander Schleicher GmbH & Co.
Segelflugzeugbau Models ASH 25M and continuing airworthiness information
(IBR) of the service information listed in this
ASH 26E gliders. This AD results from (MCAI) originated by an aviation
paragraph under 5 U.S.C. 552(a) and 1 CFR
mandatory continuing airworthiness authority of another country. The MCAI
part 51.
information (MCAI) issued by an states:
(2) You must use this service information
as applicable to do the actions required by aviation authority of another country to Occurrences were reported of finding
this AD, unless the AD specifies otherwise. identify and correct an unsafe condition cracks on exhaust silencer part number (P/N)
(i) Boeing Alert Service Bulletin 737– on an aviation product. The MCAI 800.65.0001, installed on ASK 21 Mi
describes the unsafe condition as fatigue powered sailplanes. Subsequent investigation
55A1099, Revision 1, dated October 21, 2016.
determined that the affected part is
(ii) Reserved. cracks found on the exhaust silencer.
susceptible to fatigue cracking and is also
(3) For service information identified in We are issuing this AD to require installed on other Schleicher powered
this AD, contact Boeing Commercial actions to address the unsafe condition sailplanes.
Airplanes, Attention: Contractual & Data on these products. This condition, if not corrected, could lead
Services (C&DS), 2600 Westminster Blvd., DATES: This AD is effective January 18, to heat damage in the engine compartment
MC 110–SK57, Seal Beach, CA 90740–5600; 2018. and to the engine installation, possibly
telephone 562–797–1717; internet https:// The Director of the Federal Register resulting in reduced control of the powered
www.myboeingfleet.com. sailplane.
approved the incorporation by reference
(4) You may view this service information To address this potentially unsafe
of a certain publication listed in this AD condition, Schleicher issued Technical Note
at the FAA, Transport Standards Branch, as of January 18, 2018. (TN) ASK 21 Mi No. 11, TN ASW 22 BLE 50R
1601 Lind Avenue SW, Renton, WA. For
ADDRESSES: You may examine the AD No. 16, TN ASH 25 M/Mi No. 32 and TN
information on the availability of this ASH 26 E No. 19 (single document, hereafter
docket on the internet at http://
material at the FAA, call 425–227–1221. referred to as ‘the TN’ in this [EASA] AD),
www.regulations.gov by searching for
(5) You may view this service information to provide replacement instructions.
that is incorporated by reference at the
and locating Docket No. FAA–2017–
For the reasons described above, this
National Archives and Records
0911; or in person at Document
[EASA] AD requires replacement of the
Administration (NARA). For information on Management Facility, U.S. Department affected exhaust silencer with an improved
the availability of this material at NARA, call of Transportation, Docket Operations, part and introduces installation restrictions
202–741–6030, or go to: http:// M–30, West Building Ground Floor, of a part with P/N 800.65.0001].
www.archives.gov/federal-register/cfr/ibr- Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590. The MCAI can be found in the AD
locations.html.
For service information identified in docket on the internet at https://
Issued in Renton, Washington, on this AD, contact Alexander Schleicher www.regulations.gov/
December 4, 2017. GmbH & Co. Segelflugzeugbau, document?D=FAA-2017-0911-0002.
Jeffrey E. Duven, Alexander-Schleicher-Str. 1, D–36163 Comments
Director, System Oversight Division, Aircraft Poppenhausen, Germany; phone: +49
Certification Service. (0) 06658 89–0; fax: +49 (0) 06658 89– We gave the public the opportunity to
[FR Doc. 2017–26619 Filed 12–13–17; 8:45 am] 40; internet: http://www.alexander- participate in developing this AD. We
BILLING CODE 4910–13–P schleicher.de; email: info@alexander- received no comments on the NPRM or
schleicher.de. You may view this on the determination of the cost to the
referenced service information at the public.
FAA, Policy and Innovation Division, Conclusion
sradovich on DSK3GMQ082PROD with RULES
901 Locust, Kansas City, Missouri
64106. For information on the We reviewed the relevant data and
availability of this material at the FAA, determined that air safety and the
call (816) 329–4148. It is also available public interest require adopting this AD
on the internet at http:// as proposed except for minor editorial
www.regulations.gov by searching for changes. We have determined that these
Docket No. FAA–2017–0911. minor changes:
VerDate Sep<11>2014 15:57 Dec 13, 2017 Jkt 244001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\14DER1.SGM 14DER1](https://thefederalregister.org/doc/82_FR_58948/page/5.svg)
Document Created: 2018-10-25 10:51:46
Document Modified: 2018-10-25 10:51:46
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective January 18, 2018. | |
| Contact | George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5357; fax: 562-627- 5210; email: [email protected] | |
| FR Citation | 82 FR 58709 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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