Airworthiness Directives; The Boeing Company Airplanes, 26576-26579 [2017-11624]

Download as PDF 26576 Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on May 15, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–11131 Filed 6–7–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0531; Directorate Identifier 2016–NM–178–AD; Amendment 39–18916; AD 2017–12–01] RIN 2120–AA64 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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0531. Examining the AD Docket Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767–200 series airplanes. This AD requires repetitive inspections for damage of a certain drive arm assembly, and related investigative and corrective actions if necessary. This AD was prompted by a report indicating that during an inspection associated with a flap, the extend overtravel stops on an actuator crank arm assembly were making contact with an adjacent drive arm assembly when the flaps were retracted. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 23, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 23, 2017. We must receive comments on this AD by July 24, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 asabaliauskas on DSKBBXCHB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0531; 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6447; fax: 425–917–6590; email: wayne.lockett@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We have received a report indicating that during an inspection of the outboard support assembly number 3 of the inboard flap of the left wing, an operator observed that the extend overtravel stops on the 4–5 actuator crank arm assembly were making contact with the adjacent 6–9 drive arm assembly when the flaps were totally retracted. The problem occurred with the installation of 767–400ER flaps, modified as specified in supplemental type certificate (STC) ST01329WI–D, on 767–200 airplanes. This condition, if not corrected, could result in interference between the 6–9 drive arm assembly and the 4–5 actuator crank arm assembly, which causes a fatigue load on the 5–7 link that could result in failure of the 5–7 link and subsequent PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 loss of the inboard flap. Continued safe flight and landing could be adversely affected after the departure of a flap during takeoff or landing. We are issuing this AD to correct the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 767–57A0134, dated May 27, 2016. The service information describes procedures for repetitive inspections for damage caused by interference between the 6–9 drive arm assembly and the 4– 5 actuator crank arm assembly on the inboard flap outboard support assembly number 3 and number 6, and related investigative and corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this AD and the Service Information.’’ For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0531. The phrase ‘‘related investigative actions’’ is used in this AD. Related investigative actions are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ‘‘corrective actions’’ is used in this AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This AD and the Service Information Boeing Alert Service Bulletin 767– 57A0134, dated May 27, 2016, specifies to contact the manufacturer for certain instructions, but this AD would require using repair methods, modification deviations, and alteration deviations in one of the following ways: E:\FR\FM\08JNR1.SGM 08JNR1 Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Boeing Alert Service Bulletin 767– 57A0134, dated May 27, 2016, affects eight airplanes: Those already modified by STC ST01329WI–D. This AD applies to any airplane modified by STC ST01329WI–D, including any airplanes modified in the future. We have coordinated this difference with Boeing. FAA’s Justification and Determination of the Effective Date There are currently no domestic operators of this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists 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, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2017–0531 and Directorate Identifier 2016–NM–178–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, 26577 environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance Currently, there are no affected U.S.registered airplanes. If an affected airplane is imported and placed on the U.S. Register in the future, we provide the following cost estimates to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Inspection ..................... 3 work-hours × $85 per hour = $255 per inspection cycle ..................... Cost per product $0 $255 per inspection cycle. ESTIMATED COSTS FOR OPTIONAL ACTIONS Action Labor cost 4–5 actuator crank arm assembly modification ........... 4–5 actuator crank arm assembly replacement ........... 34 work-hours × $85 per hour = $2,890 ...................... 16 work-hours × $85 per hour = $1,360 ...................... Cost per product Parts cost $0 10 $2,890 1,360 1 We have received no definitive data that would enable us to provide parts cost estimates for the 4–5 actuator crank arm assembly replacement. We estimate the following costs to do any necessary repairs 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 Labor cost 4–5 actuator crank arm assembly interim blend repair asabaliauskas on DSKBBXCHB2PROD with RULES Action 8 work-hours × $85 per hour = $680 ........................... We have received no definitive data that would enable us to provide cost estimates for the 6–9 drive arm assembly repair because the work-hours required for repair depend on the damage found. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 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 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 $680 products identified in this rulemaking action. 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, E:\FR\FM\08JNR1.SGM 08JNR1 26578 Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations (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 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): ■ 2017–12–01 The Boeing Company: Amendment 39–18916; Docket No. FAA–2017–0531; Directorate Identifier 2016–NM–178–AD. (a) Effective Date This AD is effective June 23, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 767–200 series airplanes, equipped with 767–400ER flaps modified as specified in supplemental type certificate (STC) ST01329WI–D. asabaliauskas on DSKBBXCHB2PROD with RULES (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report indicating that during an inspection associated with a flap, the extend overtravel stops on an actuator crank arm assembly were making contact with an adjacent drive arm assembly when the flaps were retracted. We are issuing this AD to detect and correct interference between a drive arm assembly and an actuator crank arm assembly, which causes a fatigue load on a certain link that could result in failure of that link and subsequent loss of the flap. Continued safe flight and landing could be adversely affected after the departure of a flap during takeoff or landing. VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the 6–9 Drive Arm Assembly and Related Investigative and Corrective Actions Except as provided by paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–57A0134, dated May 27, 2016: Do a general visual inspection of the 6–9 drive arm assembly on the left and right wing for any damage, and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–57A0134, dated May 27, 2016, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection at the interval specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–57A0134, dated May 27, 2016. (h) Optional Terminating Actions Doing the action specified in either paragraph (h)(1) or paragraph (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–57A0134, dated May 27, 2016, except as required by paragraph (i)(2) of this AD, terminates the repetitive inspections required by paragraph (g) of this AD for the drive arm assembly associated with the replacement or modification. (1) A 4–5 actuator crank arm assembly replacement. (2) A 4–5 actuator crank arm assembly modification, including all applicable related investigative and corrective actions. (i) Service Information Exceptions (1) Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–57A0134, dated May 27, 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) Where Boeing Alert Service Bulletin 767–57A0134, dated May 27, 2016, specifies to contact Boeing for appropriate action as an ‘‘RC’’ (Required for Compliance) step, this AD requires repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (i)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (k) Related Information For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6447; fax: 425– 917–6590; email: wayne.lockett@faa.gov. (l) 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 767– 57A0134, dated May 27, 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 Airplane Directorate, 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 E:\FR\FM\08JNR1.SGM 08JNR1 26579 Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on May 26, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–11624 Filed 6–7–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9490; Directorate Identifier 2016–NE–26–AD; Amendment 39– 18914; AD 2017–11–15] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6–80C2L1F turbofan engines. This AD was prompted by a reduction in the life limit of the affected engines which is the result of a revised operating profile. This AD requires replacement of the high-pressure turbine (HPT) spacer/ impeller, part number (P/N) 1539M12P02, at a newer, lower life limit. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective July 13, 2017. SUMMARY: ADDRESSES: See the FOR FURTHER INFORMATION CONTACT section. 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–2016– 9490; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document 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: Herman Mak, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7147; fax: 781–238–7199; email: herman.mak@faa.gov. 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 certain GE CF6–80C2L1F turbofan engines. The NPRM published in the Federal Register on January 23, 2017 (82 FR 7734) (‘‘the NPRM’’). The NPRM was prompted by a reduction in the life limit of the affected engines which is the result of a revised operating profile. The NPRM proposed to require replacement of the HPT spacer/impeller, P/N 1539M12P02, at a newer, lower life limit. We are issuing this AD to prevent failure of the HPT spacer/impeller, uncontained release of the HPT spacer/impeller, damage to the engine, and damage to the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Revise Compliance GE Aviation requested that we indicate in the compliance section of this AD that the affected HPT spacer/ impeller is installed on GE CF6– 80C2L1F engines only. GE Aviation commented that this P/N impeller is also installed on other models of the CF6–80C2 engine. We disagree. We believe that the applicability section is clear that this AD applies to GE CF6–80C2L1F turbofan engines with a HPT spacer/ impeller, P/N 1539M12P02, installed. We did not change this AD. Miscellaneous Comment An individual commenter indicated that the proposal showed the FAA’s commitment to ‘‘staying on top of changes in the industry.’’ The commenter noted, however, that although GE has updated the life expectancy of this part, it may still be a long time before it needs to be replaced. The commenter indicated, therefore, that the FAA’s action may be ‘‘over zealous’’ and lead to ‘‘large scale waste.’’ We disagree. We are issuing this AD to prevent failure of an engine rotating part, which could lead to failure of the part, uncontained release of the part, damage to the engine, and damage to the airplane. We did not change this AD. Support for the NPRM An individual commenter supported the NPRM. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed. Costs of Compliance We estimate that this AD affects 0 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost asabaliauskas on DSKBBXCHB2PROD with RULES Replacement of HPT spacer/impeller at reduced life. 0 work-hours × $85 per hour = $0 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 $19,320 (pro-rated cost of part) ..... rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more PO 00000 Frm 00009 Cost per product Parts cost Fmt 4700 Sfmt 4700 Cost on U.S. operators $19,320 detail the scope of the Agency’s authority. E:\FR\FM\08JNR1.SGM 08JNR1 $0

Agencies

[Federal Register Volume 82, Number 109 (Thursday, June 8, 2017)]
[Rules and Regulations]
[Pages 26576-26579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11624]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0531; Directorate Identifier 2016-NM-178-AD; 
Amendment 39-18916; AD 2017-12-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 767-200 series airplanes. This AD requires 
repetitive inspections for damage of a certain drive arm assembly, and 
related investigative and corrective actions if necessary. This AD was 
prompted by a report indicating that during an inspection associated 
with a flap, the extend overtravel stops on an actuator crank arm 
assembly were making contact with an adjacent drive arm assembly when 
the flaps were retracted. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective June 23, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 23, 
2017.
    We must receive comments on this AD by July 24, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this 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 Airplane 
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the 
availability of this material at the FAA, call 425-227-1221. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0531.

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-
0531; 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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: wayne.lockett@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received a report indicating that during an inspection of 
the outboard support assembly number 3 of the inboard flap of the left 
wing, an operator observed that the extend overtravel stops on the 4-5 
actuator crank arm assembly were making contact with the adjacent 6-9 
drive arm assembly when the flaps were totally retracted. The problem 
occurred with the installation of 767-400ER flaps, modified as 
specified in supplemental type certificate (STC) ST01329WI-D, on 767-
200 airplanes. This condition, if not corrected, could result in 
interference between the 6-9 drive arm assembly and the 4-5 actuator 
crank arm assembly, which causes a fatigue load on the 5-7 link that 
could result in failure of the 5-7 link and subsequent loss of the 
inboard flap. Continued safe flight and landing could be adversely 
affected after the departure of a flap during takeoff or landing. We 
are issuing this AD to correct the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 767-57A0134, dated May 
27, 2016. The service information describes procedures for repetitive 
inspections for damage caused by interference between the 6-9 drive arm 
assembly and the 4-5 actuator crank arm assembly on the inboard flap 
outboard support assembly number 3 and number 6, and related 
investigative and corrective actions. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between this AD and the Service Information.'' For 
information on the procedures and compliance times, see this service 
information at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2017-0531.
    The phrase ``related investigative actions'' is used in this AD. 
Related investigative actions are follow-on actions that (1) are 
related to the primary action, and (2) further investigate the nature 
of any condition found. Related investigative actions in an AD could 
include, for example, inspections.
    The phrase ``corrective actions'' is used in this AD. Corrective 
actions correct or address any condition found. Corrective actions in 
an AD could include, for example, repairs.

Differences Between This AD and the Service Information

    Boeing Alert Service Bulletin 767-57A0134, dated May 27, 2016, 
specifies to contact the manufacturer for certain instructions, but 
this AD would require using repair methods, modification deviations, 
and alteration deviations in one of the following ways:

[[Page 26577]]

     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.
    Boeing Alert Service Bulletin 767-57A0134, dated May 27, 2016, 
affects eight airplanes: Those already modified by STC ST01329WI-D. 
This AD applies to any airplane modified by STC ST01329WI-D, including 
any airplanes modified in the future. We have coordinated this 
difference with Boeing.

FAA's Justification and Determination of the Effective Date

    There are currently no domestic operators of this product. 
Therefore, we find that notice and opportunity for prior public comment 
are unnecessary and that good cause exists 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, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2017-0531 and 
Directorate Identifier 2016-NM-178-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. If an 
affected airplane is imported and placed on the U.S. Register in the 
future, we provide the following cost estimates to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
              Action                     Labor cost         Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Inspection........................  3 work-hours x $85                $0  $255 per inspection cycle.
                                     per hour = $255 per
                                     inspection cycle.
----------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
4-5 actuator crank arm assembly modification..  34 work-hours x $85 per hour =                $0          $2,890
                                                 $2,890.
4-5 actuator crank arm assembly replacement...  16 work-hours x $85 per hour =             \1\ 0           1,360
                                                 $1,360.
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide parts cost estimates for the 4-5
  actuator crank arm assembly replacement.

    We estimate the following costs to do any necessary repairs 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
----------------------------------------------------------------------------------------------------------------
4-5 actuator crank arm assembly interim blend   8 work-hours x $85 per hour =                 $0            $680
 repair.                                         $680.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the 6-9 drive arm assembly repair because the work-
hours required for repair depend on the damage found.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

Authority for This Rulemaking

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

Regulatory Findings

    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,

[[Page 26578]]

    (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):

2017-12-01 The Boeing Company: Amendment 39-18916; Docket No. FAA-
2017-0531; Directorate Identifier 2016-NM-178-AD.

(a) Effective Date

    This AD is effective June 23, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 767-200 series 
airplanes, equipped with 767-400ER flaps modified as specified in 
supplemental type certificate (STC) ST01329WI-D.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report indicating that during an 
inspection associated with a flap, the extend overtravel stops on an 
actuator crank arm assembly were making contact with an adjacent 
drive arm assembly when the flaps were retracted. We are issuing 
this AD to detect and correct interference between a drive arm 
assembly and an actuator crank arm assembly, which causes a fatigue 
load on a certain link that could result in failure of that link and 
subsequent loss of the flap. Continued safe flight and landing could 
be adversely affected after the departure of a flap during takeoff 
or landing.

(f) Compliance

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

(g) Inspection of the 6-9 Drive Arm Assembly and Related Investigative 
and Corrective Actions

    Except as provided by paragraph (i)(1) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 767-57A0134, dated May 27, 2016: Do a 
general visual inspection of the 6-9 drive arm assembly on the left 
and right wing for any damage, and all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0134, dated May 27, 2016, except as required by paragraph (i)(2) 
of this AD. Do all applicable related investigative and corrective 
actions before further flight. Repeat the inspection at the interval 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 767-57A0134, dated May 27, 2016.

(h) Optional Terminating Actions

    Doing the action specified in either paragraph (h)(1) or 
paragraph (h)(2) of this AD, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 767-57A0134, dated May 
27, 2016, except as required by paragraph (i)(2) of this AD, 
terminates the repetitive inspections required by paragraph (g) of 
this AD for the drive arm assembly associated with the replacement 
or modification.
    (1) A 4-5 actuator crank arm assembly replacement.
    (2) A 4-5 actuator crank arm assembly modification, including 
all applicable related investigative and corrective actions.

(i) Service Information Exceptions

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 767-57A0134, dated May 27, 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) Where Boeing Alert Service Bulletin 767-57A0134, dated May 
27, 2016, specifies to contact Boeing for appropriate action as an 
``RC'' (Required for Compliance) step, this AD requires repair using 
a method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (k) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) Except as required by paragraph (i)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (j)(4)(i) and 
(j)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(k) Related Information

    For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; 
fax: 425-917-6590; email: wayne.lockett@faa.gov.

(l) 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 767-57A0134, dated May 27, 
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 
Airplane Directorate, 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

[[Page 26579]]

202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 26, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-11624 Filed 6-7-17; 8:45 am]
BILLING CODE 4910-13-P