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Federal Aviation Administration (FAA), DOT.
Final rule; request for comments.
The FAA is adopting an airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD requires repetitive checks of the aileron trim actuator bearing for free rotation, repetitive detailed inspections of the aileron trim actuator attachment lug for damage and cracking, and applicable on-condition actions. This AD was prompted by a report of the failure of the aileron trim actuator attachment lug. The FAA is issuing this AD to address the unsafe condition on these products.
This AD is effective July 12, 2019.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 12, 2019.
We must receive comments on this AD by August 12, 2019.
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.
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 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 referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-0445.
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-2019-0445; 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 street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt.
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FOR FURTHER INFORMATION CONTACT:
Katherine Venegas, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5353; fax: 562-627-5210; email: firstname.lastname@example.org.
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Start Supplemental Information
The FAA received a report indicating that a flightcrew could not center the ailerons with a left or right turn on the aileron trim control wheel during a flight control check. Maintenance personnel found that the aileron trim actuator attachment lug had broken off of its support box assembly but was still attached to the aileron trim actuator. Stress analysis found that the separation of the lug could have been the result of seizure of the aileron trim actuator bearing, which would exert forces on the attachment lug that could be higher than what it is designed for. The lug failure resulted in a free-floating aileron trim actuator and subsequent loss of feel force, wheel centering, and lateral trim. This condition, if not addressed, could cause over-control of the airplane and subsequent lateral pilot induced oscillations (PIO), which could adversely affect continued safe flight and landing.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 757-27A0159 RB, dated March 29, 2019. This service information describes procedures for repetitive checks of the aileron trim actuator bearing for free rotation, repetitive detailed inspections of the aileron trim actuator attachment lug for damage or cracking, and applicable on-condition actions. On-condition actions include high frequency eddy current (HFEC) inspections of the aileron trim actuator attachment lug for cracking, repair and replacement. 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.
The FAA is issuing this AD because the agency 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.
This AD requires accomplishment of the actions identified in Boeing Alert Requirements Bulletin 757-27A0159 RB, dated March 29, 2019, described previously, except for any differences identified as exceptions in the regulatory text of this AD.
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-2019-0445.
The FAA considers this AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, the Start Printed Page 30578FAA might consider additional rulemaking.
Justification for Immediate Adoption and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies forgoing notice and comment prior to adoption of this rule because failure of the aileron trim actuator attachment lug, if not addressed, could cause over-control of the airplane and subsequent lateral PIO, which could adversely affect continued safe flight and landing.
The compliance time for the required action of this AD is 1,760 flight hours (approximately 149 days for certain airplanes). Issuing a notice of proposed rulemaking (NPRM) would require time to allow for public comment, and time for the FAA to consider and respond to those comments. As a result, the time allowed for operators to comply with the AD within acceptable risk parameters would be significantly reduced, possibly grounding airplanes. Additionally, reducing the compliance time could substantially disrupt certain operators. Accordingly, notice and opportunity for prior public comment are impracticable and contrary to public interest pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the reasons stated above, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days.
This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, the FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA-2019-0445 and Product Identifier 2019-NM-083-AD at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments.
The FAA will post all comments received, without change, to http://www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact received about this final rule.
Costs of Compliance
The FAA estimates that this AD affects 451 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
|Action||Labor cost||Parts cost||Cost per product||Cost on U.S. operators|
|Repetitive inspections||3 work-hours × $85 per hour = $255 per inspection cycle||$0||$255 per inspection cycle||$115,005 per inspection cycle.|
The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of the inspection. The FAA has no way of determining the number of aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Costs
|Action||Labor cost||Parts cost||Cost per product|
|Replacement||4 work-hours × $85 per hour = $340||$17,693||$18,033|
|HFEC inspection||1 work-hour × $85 per hour = $85||0||85|
The FAA has received no definitive data that would enable us to provide cost estimates for the on-condition repairs specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. “Subtitle VII: Aviation Programs” describes in more detail the scope of the Agency's authority.
The FAA is 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 and associated appliances to the Director of the System Oversight Division.
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) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities Start Printed Page 30579under the criteria of the Regulatory Flexibility Act.
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- Air transportation
- Aviation safety
- Incorporation by reference
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
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1. The authority citation for part 39 continues to read as follows: End Amendment Part
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2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): End Amendment Part
2019-12-13 The Boeing Company: Amendment 39-19668; Docket No. FAA-2019-0445; Product Identifier 2019-NM-083-AD.
(a) Effective Date
This AD is effective July 12, 2019.
(b) Affected ADs
This AD applies to all The Boeing Company Model 757-200, -200PF, -200CB, and -300 series airplanes, certificated in any category.
Air Transport Association (ATA) of America Code 27, Flight controls.
(e) Unsafe Condition
This AD was prompted by a report of the failure of the aileron trim actuator attachment lug. The FAA is issuing this AD to address failure of the aileron trim actuator attachment lug and subsequent loss of feel force, wheel centering, and lateral trim. This condition, if not corrected, could cause over-control of the airplane and subsequent lateral pilot induced oscillations (PIO), which could adversely affect continued safe flight and landing.
Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions
Except as specified by paragraph (h) of this AD: At the applicable times specified in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 757-27A0159 RB, dated March 29, 2019, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757-27A0159 RB, dated March 29, 2019.
Note 1 to paragraph (g):
Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 757-27A0159, dated March 29, 2019, which is referred to in Boeing Alert Requirements Bulletin 757-27A0159 RB, dated March 29, 2019.
(h) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements of this AD: Where Boeing Alert Requirements Bulletin 757-27A0159 RB, dated March 29, 2019, uses the phrase “the original issue date of the Requirements Bulletin 757-27A0159 RB,” this AD requires using “the effective date of this AD.”
(2) Where Boeing Alert Requirements Bulletin 757-27A0159 RB, dated March 29, 2019, specifies contacting Boeing for repair instructions: This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
(i) 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 (j) 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 Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, FAA, 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.
(j) Related Information
For more information about this AD, contact Katherine Venegas, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5353; fax: 562-627-5210; email: email@example.com.
(k) 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 Requirements Bulletin 757-27A0159 RB, dated March 29, 2019.
(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, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195.
(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.
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Issued in Des Moines, Washington, on June 18, 2019.
Acting Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2019-13514 Filed 6-26-19; 8:45 am]
BILLING CODE 4910-13-P