Airworthiness Directives; The Boeing Company Airplanes, 35655-35657 [2016-12849]

Download as PDF Federal Register / Vol. 81, No. 107 / Friday, June 3, 2016 / Proposed Rules Novel or Unusual Design Features The BHTI Model 525 helicopter will incorporate the following novel or unusual design features: an advanced CAS system. The novel design includes the integration of audio and visual alerts, tactical sensors, and CAS message consolidation. The new technologies associated with integrated visual, aural, tactile, and alert messaging are more effective in alerting the flightcrew and aiding them in decisionmaking than the discrete colored lights for warning, caution, and advisory alerts prescribed in § 29.1322 alone. Discussion The current 14 CFR part 29 standards do not provide adequate standards for the advanced CAS system of the Bell Model 525 helicopter due to the complexity of the aircraft systems and the modes of the fly by wire primary flight controls. The proposed special condition will update definitions, define a prioritization scheme, expand color requirements, and address performance for flightcrew alerting to reflect changes in technology and functionality. Applicability As discussed above, these special conditions are applicable to the BHTI Model 525 helicopter. Should BHTI apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one model of helicopter. It is not a rule of general applicability. List of Subjects in 14 CFR Part 29 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. mstockstill on DSK3G9T082PROD with PROPOSALS The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for Bell Helicopter Textron, Inc., Model 525 helicopters. Flightcrew Alerting (a) Flightcrew alerts must: (1) Provide the flightcrew with the information needed to: VerDate Sep<11>2014 21:06 Jun 02, 2016 Jkt 238001 (i) Identify non-normal operation or aircraft system conditions, and (ii) Determine the appropriate actions, if any. (2) Be readily and easily detectable and intelligible by the flightcrew under all foreseeable operating conditions, including conditions where multiple alerts are provided. (3) Be removed when the alerting condition no longer exists. (b) Alerts must conform to the following prioritization hierarchy based on the urgency of flightcrew awareness and response. (1) Warning: For conditions that require immediate flightcrew awareness and immediate flightcrew response. (2) Caution: For conditions that require immediate flightcrew awareness and subsequent flightcrew response. (3) Advisory: For conditions that require flightcrew awareness and may require subsequent flightcrew response. (c) Warning and caution alerts must: (1) Be prioritized within each category, when necessary. (2) Provide timely attention-getting cues through at least two different senses by a combination of aural, visual, or tactile indications. (3) Permit each occurrence of the attention-getting cues required by paragraph (c)(2) of these special conditions to be acknowledged and suppressed, unless they are required to be continuous. (d) The alert function must be designed to minimize the effects of false and nuisance alerts. In particular, it must be designed to: (1) Prevent the presentation of an alert that is inappropriate or unnecessary. (2) Provide a means to suppress an attention-getting component of an alert caused by a failure of the alerting function that interferes with the flightcrew’s ability to safely operate the helicopter. This means must not be readily available to the flightcrew so that it could be operated inadvertently or by habitual reflexive action. When an alert is suppressed, there must be a clear and unmistakable annunciation to the flightcrew that the alert has been suppressed. (e) Visual alert indications must: (1) Conform to the following color convention: (i) Red for warning alert indications. (ii) Amber or yellow for caution alert indications. (iii) Any color except red, amber, yellow, or green for advisory alert indications. (2) Use visual coding techniques, together with other alerting function elements in the cockpit, to distinguish between warning, caution, and advisory PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 35655 alert indications, if they are presented on monochromatic displays that are not capable of conforming to the color convention in paragraph (e)(1) of these special conditions. (f) Use of the colors red, amber, and yellow in the cockpit for functions other than flightcrew alerting must be limited and must not adversely affect flightcrew alerting. Issued in Fort Worth, Texas, on May 24, 2016. Lance T. Gant Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–13148 Filed 6–2–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6672; Directorate Identifier 2016–NM–022–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 787–8 airplanes. This proposed AD was prompted by a report that the grounding jumper between the environmental control system (ECS) bracket and the current return network (CRN) strap near passenger 1 left and 1 right entry doors was not bonded correctly during manufacturing. This proposed AD would require changing the configuration of the grounding jumpers connecting the ECS brackets and CRN straps; measuring the bond resistance; and related investigative and corrective actions if necessary. We are proposing this AD to prevent an incorrectly bonded jumper between the ECS bracket and the CRN strap, which does not provide proper grounding to the door frames at door 1 left and 1 right. If a fault occurs, an electrical shock hazard can exist to passengers and flight crew and could result in personal or fatal injury. DATES: We must receive comments on this proposed AD by July 18, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\03JNP1.SGM 03JNP1 35656 Federal Register / Vol. 81, No. 107 / Friday, June 3, 2016 / Proposed Rules • 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 NPRM, 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–2016– 6672. 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–2016– 6672; 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: Brendan Shanley, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6492; fax: 425–917–6590; email: brendan.shanley@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– 2016–6672; Directorate Identifier 2016– NM–022–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. Discussion We have received a report that the grounding jumper between the ECS bracket and the CRN strap near passenger1 left and 1 right entry doors was not bonded correctly during manufacturing. Engineering documentation did not include applying an electrical bond between the ECS bracket and CRN strap. The existing bond configuration does not ground the door frame structure in the event of an electrical equipment fault. This condition, if not corrected, could result in an electrical shock hazard to passengers and flight crew and could result in personal or fatal injury. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin B787–81205–SB530025–00, Issue 001, dated July 17, 2014. The service information describes procedures for changing the configuration of the grounding jumpers connecting the ECS brackets and CRN straps; measuring the bond resistance; and related investigative and corrective actions if necessary. 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 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 the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. For information on the procedures, see this service information at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–6672. The phrase ‘‘related investigative actions’’ is used in this proposed AD. Related investigative actions are followon 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 proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Costs of Compliance We estimate that this proposed AD affects 6 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators Installation ............................... mstockstill on DSK3G9T082PROD with PROPOSALS Action 6 work-hours × $85 per hour = $510 ..................................... $100 $610 $3,660 We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby VerDate Sep<11>2014 21:06 Jun 02, 2016 Jkt 238001 reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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 E:\FR\FM\03JNP1.SGM 03JNP1 Federal Register / Vol. 81, No. 107 / Friday, June 3, 2016 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: mstockstill on DSK3G9T082PROD with PROPOSALS ■ 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): ■ The Boeing Company: Docket No. FAA– 2016–6672; Directorate Identifier 2016– NM–022–AD. VerDate Sep<11>2014 21:06 Jun 02, 2016 Jkt 238001 (a) Comments Due Date We must receive comments by July 18, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787–8 airplanes, certificated in any category, as identified in Boeing Service Bulletin B787–81205–SB530025–00, Issue 001, dated July 17, 2014. (d) Subject Air Transport Association (ATA) of America Code 53; Fuselage. (e) Unsafe Condition This AD was prompted by a report that the grounding jumper between the environmental control system (ECS) bracket and the current return network (CRN) strap near passenger 1 left and 1 right entry doors was not bonded correctly during manufacturing. We are issuing this AD to prevent an incorrectly bonded jumper between the ECS bracket and the CRN strap, which does not provide proper grounding to the door frames at door 1 left and 1 right. If a fault occurs, an electrical shock hazard can exist to passengers and flight crew and could result in personal or fatal injury. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Grounding Jumper Revision Within 12 months after the effective date of this AD: Change the configuration of the grounding jumpers connecting the ECS brackets and CRN straps, including measuring the bond resistance and doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin B787–81205–SB530025–00, Issue 001, dated July 17, 2014. Do all applicable related investigative and corrective actions before further flight. (h) 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 (i)(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 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 35657 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. (i) Related Information (1) For more information about this AD, contact Brendan Shanley, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6492; fax: 425–917–6590; email: brendan.shanley@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 May 20, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–12849 Filed 6–2–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6673; Directorate Identifier 2015–NM–092–AD] RIN 2120–AA64 Airworthiness Directives; Ameri-King Corporation Emergency Locator Transmitters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Ameri-King Corporation emergency locator transmitters (ELTs) as installed on various aircraft. This proposed AD was prompted by multiple reports of ELT failure. This proposed AD was also prompted by a report of noncompliance to quality standards and manufacturer processes related to Ameri-King Corporation ELTs. Failure to adhere to these standards and processes could result in ELTs that do not function. This proposed AD would require repetitive SUMMARY: E:\FR\FM\03JNP1.SGM 03JNP1

Agencies

[Federal Register Volume 81, Number 107 (Friday, June 3, 2016)]
[Proposed Rules]
[Pages 35655-35657]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12849]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6672; Directorate Identifier 2016-NM-022-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 787-8 airplanes. This proposed AD was 
prompted by a report that the grounding jumper between the 
environmental control system (ECS) bracket and the current return 
network (CRN) strap near passenger 1 left and 1 right entry doors was 
not bonded correctly during manufacturing. This proposed AD would 
require changing the configuration of the grounding jumpers connecting 
the ECS brackets and CRN straps; measuring the bond resistance; and 
related investigative and corrective actions if necessary. We are 
proposing this AD to prevent an incorrectly bonded jumper between the 
ECS bracket and the CRN strap, which does not provide proper grounding 
to the door frames at door 1 left and 1 right. If a fault occurs, an 
electrical shock hazard can exist to passengers and flight crew and 
could result in personal or fatal injury.

DATES: We must receive comments on this proposed AD by July 18, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 35656]]

     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 NPRM, 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-2016-6672.

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-2016-
6672; 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: Brendan Shanley, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6492; fax: 425-917-6590; email: 
brendan.shanley@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-2016-6672; 
Directorate Identifier 2016-NM-022-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.

Discussion

    We have received a report that the grounding jumper between the ECS 
bracket and the CRN strap near passenger1 left and 1 right entry doors 
was not bonded correctly during manufacturing. Engineering 
documentation did not include applying an electrical bond between the 
ECS bracket and CRN strap. The existing bond configuration does not 
ground the door frame structure in the event of an electrical equipment 
fault. This condition, if not corrected, could result in an electrical 
shock hazard to passengers and flight crew and could result in personal 
or fatal injury.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin B787-81205-SB530025-00, Issue 
001, dated July 17, 2014. The service information describes procedures 
for changing the configuration of the grounding jumpers connecting the 
ECS brackets and CRN straps; measuring the bond resistance; and related 
investigative and corrective actions if necessary. 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 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 the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously. For information on the 
procedures, see this service information at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-6672.
    The phrase ``related investigative actions'' is used in this 
proposed 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 proposed AD. 
Corrective actions correct or address any condition found. Corrective 
actions in an AD could include, for example, repairs.

Costs of Compliance

    We estimate that this proposed AD affects 6 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per      Cost on  U.S.
              Action                        Labor cost            Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Installation......................  6 work-hours x $85 per               $100             $610           $3,660
                                     hour = $510.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    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 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

[[Page 35657]]

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-2016-6672; Directorate Identifier 
2016-NM-022-AD.

(a) Comments Due Date

    We must receive comments by July 18, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes, 
certificated in any category, as identified in Boeing Service 
Bulletin B787-81205-SB530025-00, Issue 001, dated July 17, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 53; Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report that the grounding jumper 
between the environmental control system (ECS) bracket and the 
current return network (CRN) strap near passenger 1 left and 1 right 
entry doors was not bonded correctly during manufacturing. We are 
issuing this AD to prevent an incorrectly bonded jumper between the 
ECS bracket and the CRN strap, which does not provide proper 
grounding to the door frames at door 1 left and 1 right. If a fault 
occurs, an electrical shock hazard can exist to passengers and 
flight crew and could result in personal or fatal injury.

(f) Compliance

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

(g) Grounding Jumper Revision

    Within 12 months after the effective date of this AD: Change the 
configuration of the grounding jumpers connecting the ECS brackets 
and CRN straps, including measuring the bond resistance and doing 
all applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin B787-81205-SB530025-00, Issue 001, dated July 17, 2014. Do 
all applicable related investigative and corrective actions before 
further flight.

(h) 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 (i)(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.

(i) Related Information

    (1) For more information about this AD, contact Brendan Shanley, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6492; fax: 425-917-6590; 
email: brendan.shanley@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 May 20, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12849 Filed 6-2-16; 8:45 am]
 BILLING CODE 4910-13-P
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