Airworthiness Directives; The Boeing Company Airplanes, 39239-39241 [2019-17008]

Download as PDF Federal Register / Vol. 84, No. 154 / Friday, August 9, 2019 / Proposed Rules Applicability As discussed above, these special conditions are applicable to Boeing Model 737 series airplanes. Should Boeing apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only one novel or unusual design feature on one model series of airplanes. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. Authority Citation The authority citation for these special conditions is as follows: khammond on DSKBBV9HB2PROD with PROPOSALS Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702, 44704. The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for Boeing Model 737 series airplanes. In addition to the requirements of § 25.562, passenger seats incorporating an inertia locking device (ILD) must meet the following: 1. Level of Protection Provided by ILD—It must be demonstrated by test that the seats and attachments, when subject to the emergency-landing dynamic conditions specified in § 25.562, and with one ILD not deployed, do not experience structural failure that could result in: a. Separation of the seat from the airplane floor. b. Separation of any part of the seat that could form a hazard to the seat occupant or any other airplane occupant. c. Failure of the occupant restraint or any other condition that could result in the occupant separating from the seat. 2. Protection Provided Below and Above the ILD Actuation Condition—If step-change effects on occupant protection exist for impacts below and above that at which the ILD deploys, tests must be performed to demonstrate that the occupant is shown to be protected at any condition at which the ILD does or does not deploy, up to the maximum severity pulse specified by § 25.562. Test conditions must take into account any necessary tolerances for deployment. 3. Protection Over a Range of Crash Pulse Vectors—The ILD must be shown VerDate Sep<11>2014 15:57 Aug 08, 2019 Jkt 247001 to function as intended for all test vectors specified in § 25.562. 4. Protection During Secondary Impacts—The ILD activation setting must be demonstrated to maximize the probability of the protection being available when needed, considering a secondary impact that is above the severity at which the device is intended to deploy up to the impact loading required by § 25.562. 5. Protection of Occupants other than 50th Percentile—Protection of occupants for a range of stature from a two-year-old child to a ninety-five percentile male must be shown. 6. Inadvertent Operation—It must be shown that any inadvertent operation of the ILD does not affect the performance of the device during a subsequent emergency landing. 7. Installation Protection—It must be shown that the ILD installation is protected from contamination and interference from foreign objects. 8. Reliability—The performance of the ILD must not be altered by the effects of wear, manufacturing tolerances, aging/ drying of lubricants, and corrosion. 9. Maintenance and Functional Checks—The design, installation and operation of the ILD must be such that it is possible to functionally check the device in place. Additionally, a functional check method and a maintenance check interval must be included in the seat installer’s instructions for continued airworthiness (ICA) document. 10. Release Function—If a means exists to release an inadvertently activated ILD, the release means must not introduce additional hidden failures that would prevent the ILD from functioning properly. Issued in Des Moines, Washington, on August 5, 2019. Victor Wicklund, Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2019–17050 Filed 8–8–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0583; Product Identifier 2019–NM–063–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 39239 Notice of proposed rulemaking (NPRM). ACTION: The FAA proposes to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This proposed AD was prompted by a report of an escapement from the wing spar terminal fitting supplier indicating that the engineering requirements provided by Boeing for controlling machine mismatch were incorrect for part faying surfaces, which can result in a reduced fatigue capability at the interface of the side of body (SOB) rib. This proposed AD would require repetitive inspections for fatigue cracking and applicable oncondition actions for the SOB rib webs where fastener locations attach the terminal fittings. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by September 23, 2019. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to 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 NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231– 3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2019–0583. SUMMARY: Examining the AD Docket You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0583; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. E:\FR\FM\09AUP1.SGM 09AUP1 39240 Federal Register / Vol. 84, No. 154 / Friday, August 9, 2019 / Proposed Rules The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3528; email: Allen.Rauschendorfer@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites 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–2019–0583; Product Identifier 2019–NM–063–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. The FAA will post all comments received, without change, to http:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact received about this proposed AD. Discussion The FAA received a report of an escapement from the wing spar terminal fitting supplier indicating that the engineering requirements provided by Boeing for controlling machine mismatch were incorrect for part faying surfaces, which can result in a reduced fatigue capability at the interface of the SOB rib. The engineering-defined machined mismatch requirement of 0.001 inch was incorrectly documented as 0.010 inch. Inspection of parts internal to Boeing production found machine mismatch on faying surfaces exceeding the 0.001-inch requirement. This condition, if not addressed, could result in undetected fatigue cracks. Undetected fatigue cracks can grow to weaken primary wing structure where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 The FAA reviewed Boeing Alert Requirements Bulletin B787–81205– SB570036–00 RB, Issue 001, dated December 14, 2018. The service information describes procedures for repetitive high frequency eddy current or ultrasonic inspections for fatigue cracking and applicable on-condition actions for the SOB rib webs where fastener locations attach the terminal fittings. On-condition actions include repair. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination The FAA is proposing this AD because the agency evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishment of the actions identified in Boeing Alert Requirements Bulletin B787–81205–SB570036–00 RB, Issue 001, dated December 14, 2018, described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0583. Costs of Compliance The FAA estimates that this proposed AD affects 1 airplane of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: khammond on DSKBBV9HB2PROD with PROPOSALS ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Inspection ............... Up to 32 work-hours × $85 per hour = Up to $2,720 per inspection cycle. The FAA has received no definitive data that would enable the agency to provide cost estimates for the oncondition actions specified in this proposed AD. According to the manufacturer, some or all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all known 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 VerDate Sep<11>2014 16:41 Aug 08, 2019 Jkt 247001 Parts cost $960 Cost per product Cost on U.S. operators Up to $3,680 per inspection cycle Up to $3,680 per inspection cycle. the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not E:\FR\FM\09AUP1.SGM 09AUP1 Federal Register / Vol. 84, No. 154 / Friday, August 9, 2019 / Proposed Rules 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) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities 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: ■ 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– 2019–0583; Product Identifier 2019– NM–063–AD. (a) Comments Due Date The FAA must receive comments by September 23, 2019. (b) Affected ADs None. khammond on DSKBBV9HB2PROD with PROPOSALS (c) Applicability This AD applies to The Boeing Company Model 787–8 airplanes, certificated in any category, as identified in Boeing Alert Requirements Bulletin B787–81205– SB570036–00 RB, Issue 001, dated December 14, 2018. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report of an escapement from the wing spar terminal fitting supplier indicating that the engineering requirements provided by Boeing for controlling machine mismatch were incorrect for part faying surfaces, which can result in a reduced fatigue capability at the interface of the side of body (SOB) rib. The VerDate Sep<11>2014 15:57 Aug 08, 2019 Jkt 247001 FAA is issuing this AD to address fatigue cracks in the left and right SOB rib webs common to the front and rear wing spar terminal fittings. Undetected fatigue cracks can grow to weaken primary wing structure where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified by paragraph (h) of this AD: At the applicable times specified in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin B787–81205– SB570036–00 RB, Issue 001, dated December 14, 2018, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin B787–81205– SB570036–00 RB, Issue 001, dated December 14, 2018. Note 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin B787–81205–SB570036–00, Issue 001, dated December 14, 2018, which is referred to in Boeing Alert Requirements Bulletin B787–81205–SB570036–00 RB, Issue 001, dated December 14, 2018. (h) Exception to Service Information Specifications Where Boeing Alert Requirements Bulletin B787–81205–SB570036–00 RB, Issue 001, dated December 14, 2018, specifies contacting Boeing for repair instructions: This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9ANM-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 Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 39241 (j) Related Information (1) For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231– 3528; email: Allen.Rauschendorfer@faa.gov. (2) 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. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on July 26, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–17008 Filed 8–8–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0602; Product Identifier 2019–NM–016–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2010–26–01, which applies to certain The Boeing Company Model 777–200 series airplanes. AD 2010–26–01 requires installing a new insulation blanket on the latch beam firewall of each thrust reverser (T/R) half. Since AD 2010–26–01 was issued, the agency received a report that the T/R affected by AD 2010–26–01 has the potential to be installed on airplanes outside of the applicability of that AD. This proposed AD would retain the requirements of 2010–26–01. This proposed AD would also add airplanes to the applicability. For those airplanes, this proposed AD would require an inspection to determine if the installed T/R has an affected part number and, if an affected part number is found, installation of a new insulation blanket. The FAA is proposing this AD to address the unsafe condition on these products. SUMMARY: E:\FR\FM\09AUP1.SGM 09AUP1

Agencies

[Federal Register Volume 84, Number 154 (Friday, August 9, 2019)]
[Proposed Rules]
[Pages 39239-39241]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-17008]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0583; Product Identifier 2019-NM-063-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain The Boeing Company Model 787-8 airplanes. This proposed AD 
was prompted by a report of an escapement from the wing spar terminal 
fitting supplier indicating that the engineering requirements provided 
by Boeing for controlling machine mismatch were incorrect for part 
faying surfaces, which can result in a reduced fatigue capability at 
the interface of the side of body (SOB) rib. This proposed AD would 
require repetitive inspections for fatigue cracking and applicable on-
condition actions for the SOB rib webs where fastener locations attach 
the terminal fittings. The FAA is proposing this AD to address the 
unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by September 
23, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to 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 NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may 
view this referenced service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195. It 
is also available on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2019-0583.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0583; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

[[Page 39240]]

The AD docket contains this NPRM, the regulatory evaluation, any 
comments received, and other information. The street address for Docket 
Operations is listed above. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th 
St., Des Moines, WA 98198; phone and fax: 206-231-3528; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites 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-2019-0583; 
Product Identifier 2019-NM-063-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    The FAA will post all comments received, without change, to http://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this proposed AD.

Discussion

    The FAA received a report of an escapement from the wing spar 
terminal fitting supplier indicating that the engineering requirements 
provided by Boeing for controlling machine mismatch were incorrect for 
part faying surfaces, which can result in a reduced fatigue capability 
at the interface of the SOB rib. The engineering-defined machined 
mismatch requirement of 0.001 inch was incorrectly documented as 0.010 
inch. Inspection of parts internal to Boeing production found machine 
mismatch on faying surfaces exceeding the 0.001-inch requirement. This 
condition, if not addressed, could result in undetected fatigue cracks. 
Undetected fatigue cracks can grow to weaken primary wing structure 
where it cannot sustain limit load, which could adversely affect the 
structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018. The service 
information describes procedures for repetitive high frequency eddy 
current or ultrasonic inspections for fatigue cracking and applicable 
on-condition actions for the SOB rib webs where fastener locations 
attach the terminal fittings. On-condition actions include repair.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

    The FAA is proposing this AD because the agency evaluated all the 
relevant information and determined the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

Proposed AD Requirements

    This proposed AD would require accomplishment of the actions 
identified in Boeing Alert Requirements Bulletin B787-81205-SB570036-00 
RB, Issue 001, dated December 14, 2018, described previously, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD.
    For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2019-0583.

Costs of Compliance

    The FAA estimates that this proposed AD affects 1 airplane of U.S. 
registry. The FAA estimates the following costs to comply with this 
proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
            Action                   Labor cost         Parts cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection....................  Up to 32 work-hours             $960  Up to $3,680 per      Up to $3,680 per
                                 x $85 per hour = Up                   inspection cycle.     inspection cycle.
                                 to $2,720 per
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the on-condition actions specified 
in this proposed AD.
    According to the manufacturer, some or all of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. The FAA does not control warranty 
coverage for affected individuals. As a result, the FAA has included 
all known 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.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not

[[Page 39241]]

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) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities 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-2019-0583; Product Identifier 
2019-NM-063-AD.

(a) Comments Due Date

    The FAA must receive comments by September 23, 2019.

(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 Alert 
Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, dated 
December 14, 2018.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of an escapement from the wing 
spar terminal fitting supplier indicating that the engineering 
requirements provided by Boeing for controlling machine mismatch 
were incorrect for part faying surfaces, which can result in a 
reduced fatigue capability at the interface of the side of body 
(SOB) rib. The FAA is issuing this AD to address fatigue cracks in 
the left and right SOB rib webs common to the front and rear wing 
spar terminal fittings. Undetected fatigue cracks can grow to weaken 
primary wing structure where it cannot sustain limit load, which 
could adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the 
applicable times specified in the ``Compliance'' paragraph of Boeing 
Alert Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, 
dated December 14, 2018, do all applicable actions identified in, 
and in accordance with, the Accomplishment Instructions of Boeing 
Alert Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, 
dated December 14, 2018.

    Note 1 to paragraph (g):  Guidance for accomplishing the actions 
required by this AD can be found in Boeing Alert Service Bulletin 
B787-81205-SB570036-00, Issue 001, dated December 14, 2018, which is 
referred to in Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018.

(h) Exception to Service Information Specifications

    Where Boeing Alert Requirements Bulletin B787-81205-SB570036-00 
RB, Issue 001, dated December 14, 2018, specifies contacting Boeing 
for repair instructions: This AD requires doing the repair using a 
method approved in accordance with the procedures specified in 
paragraph (i) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (j)(1) of this AD. Information may be 
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing Company Organization Designation 
Authorization (ODA) that has been authorized by the Manager, Seattle 
ACO Branch, FAA, to make those findings. To be approved, the repair 
method, modification deviation, or alteration deviation must meet 
the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(j) Related Information

    (1) For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle 
ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and 
fax: 206-231-3528; email: [email protected].
    (2) 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. You may view this referenced service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on July 26, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-17008 Filed 8-8-19; 8:45 am]
 BILLING CODE 4910-13-P