Airworthiness Directives; The Boeing Company Airplanes, 30577-30579 [2019-13514]

Download as PDF 30577 Rules and Regulations Federal Register Vol. 84, No. 124 Thursday, June 27, 2019 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0445; Product Identifier 2019–NM–083–AD; Amendment 39–19668; AD 2019–12–13] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: 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. DATES: 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. 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 https://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. jspears on DSK30JT082PROD with RULES SUMMARY: VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 • 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 https://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 https:// 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. 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: katherine.venegas@faa.gov. SUPPLEMENTARY INFORMATION: Discussion 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 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 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 oncondition 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. FAA’s Determination 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. AD Requirements 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0445. Interim Action 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 E:\FR\FM\27JNR1.SGM 27JNR1 30578 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations FAA 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. Comments Invited 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 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 https:// 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. ADDRESSES 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 Repetitive inspections ............ 3 work-hours × $85 per hour = $255 per inspection cycle. The FAA estimates the following costs to do any necessary on-condition actions that would be required based on Parts cost Cost per product $0 $255 per inspection cycle ...... the results of the inspection. The FAA has no way of determining the number Cost on U.S. operators $115,005 per inspection cycle. of aircraft that might need these oncondition actions: ESTIMATED COSTS OF ON-CONDITION COSTS Action Labor cost Replacement ................................................................. HFEC inspection ........................................................... 4 work-hours × $85 per hour = $340 ........................... 1 work-hour × $85 per hour = $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. jspears on DSK30JT082PROD with RULES 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 VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 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 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Parts cost $17,693 0 Cost per product $18,033 85 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) 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 E:\FR\FM\27JNR1.SGM 27JNR1 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 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 None. (c) Applicability This AD applies to all The Boeing Company Model 757–200, –200PF, –200CB, and –300 series airplanes, certificated in any category. (d) Subject 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. jspears on DSK30JT082PROD with RULES (f) Compliance 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. VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 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-ANMLAACO-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: katherine.venegas@faa.gov. (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. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 30579 (i) Boeing Alert Requirements Bulletin 757–27A0159 RB, dated March 29, 2019. (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, 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on June 18, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–13514 Filed 6–26–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0017; Product Identifier 2018–NM–112–AD; Amendment 39–19662; AD 2019–12–07] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2007–11– 11 and AD 2017–01–11, which applied to all Airbus SAS Model A318 and Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes. AD 2007–11–11 required an inspection to determine the serial number of both main landing gear (MLG) sliding tubes, repetitive inspections for cracking of the affected MLG sliding tubes and corrective actions if necessary, and eventual replacement of both MLG shock absorbers. AD 2017–01–11 required identification of the part number and serial number of the MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if SUMMARY: E:\FR\FM\27JNR1.SGM 27JNR1

Agencies

[Federal Register Volume 84, Number 124 (Thursday, June 27, 2019)]
[Rules and Regulations]
[Pages 30577-30579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13514]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules 
and Regulations

[[Page 30577]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0445; Product Identifier 2019-NM-083-AD; Amendment 
39-19668; AD 2019-12-13]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: 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.

DATES: 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.

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 https://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 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 https://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 https://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.

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: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    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.

FAA's Determination

    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.

AD Requirements

    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 https://www.regulations.gov by searching for and 
locating Docket No. FAA-2019-0445.

Interim Action

    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

[[Page 30578]]

FAA 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.

Comments Invited

    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 https://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
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Repetitive inspections...........  3 work-hours x $85               $0  $255 per inspection  $115,005 per
                                    per hour = $255                      cycle.               inspection cycle.
                                    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
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement...................................  4 work-hours x $85 per hour =            $17,693         $18,033
                                                 $340.
HFEC inspection...............................  1 work-hour x $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.

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) 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

[[Page 30579]]

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):

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

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200PF, 
-200CB, and -300 series airplanes, certificated in any category.

(d) Subject

    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.

(f) Compliance

    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: [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 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 protected].

(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.
    (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, 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on June 18, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-13514 Filed 6-26-19; 8:45 am]
 BILLING CODE 4910-13-P

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