Airworthiness Directives; The Boeing Company Airplanes, 79735-79738 [2015-32055]

Download as PDF 79735 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules National banks Subject State non-member banks State member banks Federal savings associations State savings associations BHCs & FHCs SLHCs 10. Rules of Procedure All rules under this category are included in Chart A above 11. Safety and Soundness All rules under this category are included in Chart A above 12. Securities All rules under this category are included in Chart A above Dated: December 16, 2015. Thomas J. Curry, Comptroller of the Currency. By order of the Board of Governors of the Federal Reserve System, December 11, 2015. Robert deV. Frierson, Secretary of the Board. Dated: December 16, 2015. By order of the Board of Directors. Federal Deposit Insurance Corporation. Robert E. Feldman, Executive Secretary. [FR Doc. 2015–32312 Filed 12–22–15; 8:45 am] BILLING CODE P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–7525; Directorate Identifier 2015–NM–064–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–400, 747–400D, and 747–400F series airplanes; Model 757 airplanes; and Model 767 airplanes. This proposed AD was prompted by reports of uncommanded autopilot engagement events resulting in incorrect stabilizer trim adjustment during takeoff. This proposed AD would require, depending on the model/configuration for Model 747 airplanes, installing an on-ground stabilizer autotrim inhibit system, doing routine functional testing of the automatic stabilizer trim inhibit system and corrective actions if necessary; for Model 757 airplanes and Model 767 airplanes, installing relays and related asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 wiring to open and close the flight control computer (FCC) analog output that controls the stabilizer trim adjustment, doing routine functional testing of the automatic stabilizer trim inhibit system, and corrective actions if necessary; and for Model 767–300, and -300F series airplanes, installing new operational program software (OPS) into the FCCs. We are proposing this AD to prevent stabilizer mistrim, which could result in a high-speed rejected takeoff and runway overrun, or reduced controllability of the airplane after takeoff due to insufficient pitch control. DATES: We must receive comments on this proposed AD by February 8, 2016. 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 proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766–5680; 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 7525. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 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–2015– 7525; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6659; fax: 425–917–6590; email: fnu.winarto@faa.gov. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2015–7525; Directorate Identifier 2015– NM–064–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. E:\FR\FM\23DEP1.SGM 23DEP1 79736 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules Discussion We have received reports of uncommanded autopilot engagement events resulting in incorrect stabilizer trim adjustment during takeoff. The current configuration of affected airplanes allows engagement of the autopilot while on the ground. This engagement can result in the stabilizer trim being positioned to a trim setting outside of the acceptable takeoff setting range. The root cause is unknown, but the erroneous autopilot engage request is believed to have come from the mode control panel (MCP) and to have been caused by contamination within the MCP. Incorrect stabilizer trim adjustment during takeoff, if not corrected, could result in a high-speed rejected takeoff and runway overrun, or reduced controllability of the airplane after takeoff due to insufficient pitch control. Related Service Information Under 1 CFR Part 51 We reviewed the following service information. • Boeing Special Attention Service Bulletin 747–22–2256, dated March 6, 2015. This service information describes procedures for installing an on-ground stabilizer autotrim inhibit system, and doing functional testing. • Boeing Special Attention Service Bulletin 757–22–0096, dated March 23, 2015. This service information describes procedures for modifying relays and wiring to open and close the FCC analog output that controls the stabilizer trim adjustment, and doing functional testing. • Boeing Special Attention Service Bulletin 767–22–0143, Revision 1, dated July 6, 2015. This service information describes procedures for modifying relays and wiring to open and close the FCC analog output that controls the stabilizer trim adjustment, and doing functional testing. • Boeing Special Attention Service Bulletin 767–22–0146, Revision 1, dated June 25, 2015. This service information describes procedures for installing new OPS into the FCCs. 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 of this NPRM. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. 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–2015– 7525. Differences Between This Proposed AD and the Service Information For Model 747 airplanes, this proposed AD would require doing postmodification routine functional testing of the automatic stabilizer trim inhibit system, and corrective actions if necessary, at intervals not to exceed 1,500 flight hours. The service information does not require these actions. Explanation of ‘‘RC’’ Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as Required for Compliance (RC) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as RC, the following provisions apply: (1) 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, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) 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. Costs of Compliance We estimate that this proposed AD affects 1,220 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Labor cost Model 747 series airplane modification (136 airplanes). Model 747 series airplane functional test (136 airplanes). Model 757 series airplane modification (678 airplanes). Model 757 series airplane functional test (678 airplanes). Model 767 series airplane modification (406 airplanes). Model 767 series airplane software modification (23 airplanes). Model 767 series airplane functional test (406 airplanes). 123 work-hours × $85 per hour = $10,455. 4 work-hours × $85 per hour = $340 ..... $2,714 $13,169 .................. $1,790,984. 0 $340 per test .......... $46,240 per test. 83 work-hours × $85 per hour = $7,055 3,236 $10,291 .................. $6,977,298. 3 work-hours × $85 per hour = $255 per test. 121 work-hours × $85 per hour = $10,285. 1 work-hour × $85 per hour = $85 ........ 0 $255 per test .......... $172,890 per test. 6,076 $16,361 .................. $6,642,566. 0 $85 ......................... $1,955. 5 work-hours × $85 per hour = $425 per test. 0 $425 per test .......... $172,550 per test. VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 PO 00000 Frm 00018 Fmt 4702 Parts cost Sfmt 4702 Cost per product Cost on U.S. operators Action E:\FR\FM\23DEP1.SGM 23DEP1 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules According to the manufacturer, some of the costs of this proposed 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. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Authority for This Rulemaking ■ Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA– 2015–7525; Directorate Identifier 2015– NM–064–AD. (a) Comments Due Date We must receive comments by February 8, 2016. (b) Affected ADs None. (c) Applicability This AD applies to certain The Boeing Company airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(4) of this AD. (1) Model 747–400, 747–400D, and 747– 400F series airplanes, as identified in Boeing Special Attention Service Bulletin 747–22– 2256, dated March 6, 2015. (2) Model 757–200, –200PF, –200CB, and –300 series airplanes, as identified in Boeing Special Attention Service Bulletin 757–22– 0096, dated March 23, 2015. (3) Model 767–200, –300, –300F, and –400ER series airplanes, as identified in Boeing Special Attention Service Bulletin 767–22–0143, Revision 1, dated July 6, 2015. (4) Model 767–300, and –300F series airplanes, as identified in Boeing Special Attention Service Bulletin 767–22–0146, Revision 1, dated June 25, 2015. (d) Subject Air Transport Association (ATA) of America Code 22, Auto flight. (e) Unsafe Condition This AD was prompted by reports of uncommanded autopilot engagement events resulting in incorrect stabilizer trim adjustment during takeoff. We are issuing this AD to prevent stabilizer mistrim, which could result in a high-speed rejected takeoff and runway overrun, or reduced controllability of the airplane after takeoff due to insufficient pitch control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Model 747 Airplane Modification and Repetitive Functional Testing For airplanes identified in paragraph (c)(1) of this AD: Within 24 months after the effective date of this AD, install new wiring PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 79737 and relays to reroute the four autotrim arm signals through new or existing air/ground determination source select switches, and do functional testing, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–22– 2256, dated March 6, 2015. If the functional test fails, before further flight, do corrective actions, repeat the test, and do all applicable corrective actions until the functional test is passed, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–22– 2256, dated March 6, 2015. Repeat the functional test of the automatic stabilizer trim system specified in step 250. of paragraph 3.B. of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–22–2256, dated March 6, 2015, thereafter at intervals not to exceed 1,500 flight hours. If any functional test fails, before further flight, do corrective actions, repeat the test, and do all applicable corrective actions until the functional test is passed, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–22– 2256, dated March 6, 2015. (h) Model 757 Airplane Modification and Repetitive Functional Testing For airplanes identified in paragraph (c)(2) of this AD: Within 24 months after the effective date of this AD, install wiring to inhibit the automatic stabilizer trim arm discrete when the airplane is on ground, install a two-position momentary contact test switch in the main equipment center, and do the functional test and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–22– 0096, dated March 23, 2015. Repeat the functional test of the automatic stabilizer trim system and all applicable corrective actions specified in step 11. of paragraph 3.B. of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–22–0096, dated March 23, 2015, thereafter at intervals not to exceed 1,500 flight hours. (i) Model 767–200, –300, –300F, and –400ER Series Airplane Modification and Repetitive Functional Testing For airplanes identified in paragraph (c)(3) of this AD: Within 24 months after the effective date of this AD, install relays and wiring to open and close the flight control computer (FCC) analog output that controls the stabilizer trim adjustment, install a momentary action ground test switch, and do the functional testing and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–22– 0143, Revision 1, dated July 6, 2015. Repeat the functional test of the automatic stabilizer trim system and all applicable corrective actions specified in steps 5.a. through 5.g. of Paragraph 3.B. of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–22–0143, Revision 1, dated July 6, 2015, thereafter at intervals not to exceed 1,500 flight hours. E:\FR\FM\23DEP1.SGM 23DEP1 79738 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules (j) Model 767–300 and –300F Series Airplane Modification For airplanes identified in paragraph (c)(4) of this AD: Within 16 months after the effective date of this AD, install new operational program software into the FCCs, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–22–0146, Revision 1, dated June 25, 2015. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (k) Credit for Actions Accomplished in Accordance With Previous Service Information (1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 767–22–0143, dated March 6, 2015. (2) This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 767–22–0146, dated March 24, 2015. (l) 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 (m)(1) 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, 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) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) and (l)(4)(ii) 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. 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. VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 (m) Related Information (1) For more information about this AD, contact Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6659; fax: 425– 917–6590; email: fnu.winarto@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206– 544–5000, extension 1; fax: 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on December 8, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–32055 Filed 12–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0006; Directorate Identifier 2013–NM–147–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) for all Airbus Model A330–200, A330– 200 Freighter, A330–300, A340–200, and A340–300 series airplanes. The NPRM proposed to require inspecting certain trimmable horizontal stabilizer actuators (THSAs) to determine the number of total flight cycles the THSA has accumulated, and replacing the THSA if necessary. The NPRM was prompted by the results of endurance qualification tests on the THSA, which revealed a partial loss of the no-back brake (NBB) efficiency in specific load conditions. This action revises the NPRM by adding airplanes to the proposed applicability, reducing the proposed compliance times for replacing affected THSAs, and revising the definition of a serviceable THSA. We are proposing this supplemental NPRM (SNPRM) to detect and correct SUMMARY: PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 premature wear of the carbon friction disks on the NBB of the THSA, which could lead to reduced braking efficiency in certain load conditions, and, in conjunction with the inability of the power gear train to keep the ball screw in its last commanded position, could result in uncommanded movements of the trimmable horizontal stabilizer and loss of control of the airplane. Since these actions impose an additional burden over those proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: We must receive comments on this SNPRM by February 8, 2016. 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet https://www.airbus.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. 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–2014– 0006; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. E:\FR\FM\23DEP1.SGM 23DEP1

Agencies

[Federal Register Volume 80, Number 246 (Wednesday, December 23, 2015)]
[Proposed Rules]
[Pages 79735-79738]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-32055]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7525; Directorate Identifier 2015-NM-064-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 747-400, 747-400D, and 747-400F series
airplanes; Model 757 airplanes; and Model 767 airplanes. This proposed
AD was prompted by reports of uncommanded autopilot engagement events
resulting in incorrect stabilizer trim adjustment during takeoff. This
proposed AD would require, depending on the model/configuration for
Model 747 airplanes, installing an on-ground stabilizer autotrim
inhibit system, doing routine functional testing of the automatic
stabilizer trim inhibit system and corrective actions if necessary; for
Model 757 airplanes and Model 767 airplanes, installing relays and
related wiring to open and close the flight control computer (FCC)
analog output that controls the stabilizer trim adjustment, doing
routine functional testing of the automatic stabilizer trim inhibit
system, and corrective actions if necessary; and for Model 767-300, and
-300F series airplanes, installing new operational program software
(OPS) into the FCCs. We are proposing this AD to prevent stabilizer
mistrim, which could result in a high-speed rejected takeoff and runway
overrun, or reduced controllability of the airplane after takeoff due
to insufficient pitch control.

DATES: We must receive comments on this proposed AD by February 8,
2016.

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 proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-
5000, extension 1; fax: 206-766-5680; 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
7525.

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-2015-
7525; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Fnu Winarto, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6659; fax: 425-917-6590; email:
fnu.winarto@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2015-7525;
Directorate Identifier 2015-NM-064-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

[[Page 79736]]

Discussion

We have received reports of uncommanded autopilot engagement events
resulting in incorrect stabilizer trim adjustment during takeoff. The
current configuration of affected airplanes allows engagement of the
autopilot while on the ground. This engagement can result in the
stabilizer trim being positioned to a trim setting outside of the
acceptable takeoff setting range. The root cause is unknown, but the
erroneous autopilot engage request is believed to have come from the
mode control panel (MCP) and to have been caused by contamination
within the MCP. Incorrect stabilizer trim adjustment during takeoff, if
not corrected, could result in a high-speed rejected takeoff and runway
overrun, or reduced controllability of the airplane after takeoff due
to insufficient pitch control.

Related Service Information Under 1 CFR Part 51

We reviewed the following service information.
Boeing Special Attention Service Bulletin 747-22-2256,
dated March 6, 2015. This service information describes procedures for
installing an on-ground stabilizer autotrim inhibit system, and doing
functional testing.
Boeing Special Attention Service Bulletin 757-22-0096,
dated March 23, 2015. This service information describes procedures for
modifying relays and wiring to open and close the FCC analog output
that controls the stabilizer trim adjustment, and doing functional
testing.
Boeing Special Attention Service Bulletin 767-22-0143,
Revision 1, dated July 6, 2015. This service information describes
procedures for modifying relays and wiring to open and close the FCC
analog output that controls the stabilizer trim adjustment, and doing
functional testing.
Boeing Special Attention Service Bulletin 767-22-0146,
Revision 1, dated June 25, 2015. This service information describes
procedures for installing new OPS into the FCCs.
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 of this
NPRM.

FAA's Determination

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

Proposed AD Requirements

This proposed AD would require accomplishing the actions specified
in the service information described previously. 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-2015-
7525.

Differences Between This Proposed AD and the Service Information

For Model 747 airplanes, this proposed AD would require doing post-
modification routine functional testing of the automatic stabilizer
trim inhibit system, and corrective actions if necessary, at intervals
not to exceed 1,500 flight hours. The service information does not
require these actions.

Explanation of ``RC'' Steps in Service Information

The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which steps in the service information are required for
compliance with an AD. Differentiating these steps from other tasks in
the service information is expected to improve an owner's/operator's
understanding of crucial AD requirements and help provide consistent
judgment in AD compliance. The steps identified as Required for
Compliance (RC) in any service information identified previously have a
direct effect on detecting, preventing, resolving, or eliminating an
identified unsafe condition.
For service information that contains steps that are labeled as RC,
the following provisions apply: (1) 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, and an AMOC is required for any
deviations to RC steps, including substeps and identified figures; and
(2) 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.

Costs of Compliance

We estimate that this proposed AD affects 1,220 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Model 747 series airplane 123 work-hours x $85 $2,714 $13,169........... $1,790,984.
modification (136 airplanes). per hour = $10,455.
Model 747 series airplane 4 work-hours x $85 per 0 $340 per test..... $46,240 per test.
functional test (136 hour = $340.
airplanes).
Model 757 series airplane 83 work-hours x $85 per 3,236 $10,291........... $6,977,298.
modification (678 airplanes). hour = $7,055.
Model 757 series airplane 3 work-hours x $85 per 0 $255 per test..... $172,890 per test.
functional test (678 hour = $255 per test.
airplanes).
Model 767 series airplane 121 work-hours x $85 6,076 $16,361........... $6,642,566.
modification (406 airplanes). per hour = $10,285.
Model 767 series airplane 1 work-hour x $85 per 0 $85............... $1,955.
software modification (23 hour = $85.
airplanes).
Model 767 series airplane 5 work-hours x $85 per 0 $425 per test..... $172,550 per test.
functional test (406 hour = $425 per test.
airplanes).
----------------------------------------------------------------------------------------------------------------

[[Page 79737]]

According to the manufacturer, some of the costs of this proposed
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.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
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.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):

The Boeing Company: Docket No. FAA-2015-7525; Directorate Identifier
2015-NM-064-AD.

(a) Comments Due Date

We must receive comments by February 8, 2016.

(b) Affected ADs

None.

This AD applies to certain The Boeing Company airplanes,
certificated in any category, identified in paragraphs (c)(1)
through (c)(4) of this AD.
(1) Model 747-400, 747-400D, and 747-400F series airplanes, as
identified in Boeing Special Attention Service Bulletin 747-22-2256,
dated March 6, 2015.
(2) Model 757-200, -200PF, -200CB, and -300 series airplanes, as
identified in Boeing Special Attention Service Bulletin 757-22-0096,
dated March 23, 2015.
(3) Model 767-200, -300, -300F, and -400ER series airplanes, as
identified in Boeing Special Attention Service Bulletin 767-22-0143,
Revision 1, dated July 6, 2015.
(4) Model 767-300, and -300F series airplanes, as identified in
Boeing Special Attention Service Bulletin 767-22-0146, Revision 1,
dated June 25, 2015.

(d) Subject

Air Transport Association (ATA) of America Code 22, Auto flight.

(e) Unsafe Condition

This AD was prompted by reports of uncommanded autopilot
engagement events resulting in incorrect stabilizer trim adjustment
during takeoff. We are issuing this AD to prevent stabilizer
mistrim, which could result in a high-speed rejected takeoff and
runway overrun, or reduced controllability of the airplane after
takeoff due to insufficient pitch control.

(f) Compliance

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

(g) Model 747 Airplane Modification and Repetitive Functional Testing

For airplanes identified in paragraph (c)(1) of this AD: Within
24 months after the effective date of this AD, install new wiring
and relays to reroute the four autotrim arm signals through new or
existing air/ground determination source select switches, and do
functional testing, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-22-
2256, dated March 6, 2015. If the functional test fails, before
further flight, do corrective actions, repeat the test, and do all
applicable corrective actions until the functional test is passed,
in accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 747-22-2256, dated March 6, 2015. Repeat
the functional test of the automatic stabilizer trim system
specified in step 250. of paragraph 3.B. of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-22-
2256, dated March 6, 2015, thereafter at intervals not to exceed
1,500 flight hours. If any functional test fails, before further
flight, do corrective actions, repeat the test, and do all
applicable corrective actions until the functional test is passed,
in accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 747-22-2256, dated March 6, 2015.

(h) Model 757 Airplane Modification and Repetitive Functional Testing

For airplanes identified in paragraph (c)(2) of this AD: Within
24 months after the effective date of this AD, install wiring to
inhibit the automatic stabilizer trim arm discrete when the airplane
is on ground, install a two-position momentary contact test switch
in the main equipment center, and do the functional test and all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 757-22-
0096, dated March 23, 2015. Repeat the functional test of the
automatic stabilizer trim system and all applicable corrective
actions specified in step 11. of paragraph 3.B. of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 757-22-0096, dated March 23, 2015, thereafter at intervals
not to exceed 1,500 flight hours.

(i) Model 767-200, -300, -300F, and -400ER Series Airplane Modification
and Repetitive Functional Testing

For airplanes identified in paragraph (c)(3) of this AD: Within
24 months after the effective date of this AD, install relays and
wiring to open and close the flight control computer (FCC) analog
output that controls the stabilizer trim adjustment, install a
momentary action ground test switch, and do the functional testing
and all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 767-22-0143, Revision 1, dated July 6, 2015. Repeat the
functional test of the automatic stabilizer trim system and all
applicable corrective actions specified in steps 5.a. through 5.g.
of Paragraph 3.B. of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 767-22-0143, Revision 1, dated
July 6, 2015, thereafter at intervals not to exceed 1,500 flight
hours.

[[Page 79738]]

(j) Model 767-300 and -300F Series Airplane Modification

For airplanes identified in paragraph (c)(4) of this AD: Within
16 months after the effective date of this AD, install new
operational program software into the FCCs, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 767-22-0146, Revision 1, dated June 25, 2015.

(k) Credit for Actions Accomplished in Accordance With Previous Service
Information

(1) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before the
effective date of this AD using Boeing Special Attention Service
Bulletin 767-22-0143, dated March 6, 2015.
(2) This paragraph provides credit for actions required by
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using Boeing Special Attention Service
Bulletin 767-22-0146, dated March 24, 2015.

(l) 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 (m)(1) 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) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(l)(4)(i) and (l)(4)(ii) 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. 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.

(m) Related Information

(1) For more information about this AD, contact Fnu Winarto,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA,
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6659; fax: 425-917-6590;
email: fnu.winarto@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.

Issued in Renton, Washington, on December 8, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-32055 Filed 12-22-15; 8:45 am]
BILLING CODE 4910-13-P

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