Airworthiness Directives; The Boeing Company Airplanes, 58636-58638 [2019-23788]

Download as PDF 58636 Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2019– 0167. (h) Exception to EASA AD 2019–0167 The ‘‘Remarks’’ section of EASA AD 2019– 0167 does not apply to this AD. (i) No Reporting Requirement Although the service information referenced in EASA AD 2019–0167 specifies to submit certain information to the manufacturer, and specifies that action as ‘‘RC’’ (required for compliance), this AD does not include that requirement. khammond on DSKJM1Z7X2PROD with PROPOSALS (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards 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 International Section, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): For any service information referenced in EASA AD 2019–0167 that contains RC procedures and tests: Except as required by paragraph (2) of EASA AD 2019–0167 and paragraphs (i) and (j)(2) of this AD, RC procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified 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 procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. VerDate Sep<11>2014 19:05 Oct 31, 2019 Jkt 250001 (k) Related Information (1) For information about EASA AD 2019– 0167, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; email ADs@ easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. You may view this material 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. This material may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2019–0861. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. Issued in Des Moines, Washington, on October 24, 2019. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–23867 Filed 10–31–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0719; Product Identifier 2019–NM–137–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 adopt a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This proposed AD was prompted by a report of failure of a wing strut leak test due to a missing bolt on the firewall. This proposed AD would require a one-time leak test of the strut upper spar areas for the left and right wing struts, and corrective action if necessary. 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 December 16, 2019. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 • 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: 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 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. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0719; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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: Tak Kobayashi, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206– 231–3553; email: takahisa.kobayashi@ 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–2019–0719; Product Identifier 2019–NM–137–AD’’ at the beginning of your comments. The agency 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 https:// E:\FR\FM\01NOP1.SGM 01NOP1 58637 Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Discussion The FAA received a report indicating failure of a wing strut leak test due to a missing bolt on the firewall. Failure during manufacture to install a bolt that plugs a strut firewall penetration would result in a hole in the firewall. This condition, if not addressed, could allow flammable fluid leakage in the strut area. This leakage could overwhelm the drainage provision, enter the engine compartment, and result in an uncontrollable engine fire and consequent structural failure of the wing. Proposed AD Requirements 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. Costs of Compliance This proposed AD would require a one-time leak test of the strut upper spar areas for the left and right wing struts, and corrective action if necessary. The FAA estimates that this proposed AD would affect 2 airplanes of U.S. registry. The agency estimates the following costs to comply with this proposed AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 3 work-hours × $85 per hour = $255 .......................................................................................... $0 $255 $510 The FAA estimates the following costs to do any necessary on-condition action that would be required based on the results of any proposed actions. The FAA has no way of determining the number of aircraft that might need this on-condition action: ESTIMATED COSTS OF ON-CONDITION ACTION Labor cost Parts cost Cost per product 1 work-hour × $85 per hour = $85 ............................................. Minimal ....................................................................................... $85 khammond on DSKJM1Z7X2PROD with PROPOSALS 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 VerDate Sep<11>2014 19:05 Oct 31, 2019 Jkt 250001 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 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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– 2019–0719; Product Identifier 2019– NM–137–AD. (a) Comments Due Date The FAA must receive comments by December 16, 2019. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787–8 airplanes, certificated in any category, line numbers 6, 11, 17, 19, 20, 21, 23, 25 through 30 inclusive, and 32 through 38 inclusive. E:\FR\FM\01NOP1.SGM 01NOP1 58638 Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/Pylons. (e) Unsafe Condition This AD was prompted by a report of failure of a wing strut leak test due to a missing bolt on the firewall. The FAA is issuing this AD to address a hole in the firewall, which could allow flammable fluid leakage in the strut area. This leakage could overwhelm the drainage provision, enter the engine compartment, and result in an uncontrollable engine fire and consequent structural failure of the wing. khammond on DSKJM1Z7X2PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Leak Test and Corrective Action Within 12 months after the effective date of this AD: Do a one-time leak (functional) test of the strut upper spar areas for the left and right wing struts, by doing the actions specified in paragraphs (g)(1) through (5) of this AD. A review of airplane maintenance records is acceptable in lieu of this test if it can be conclusively determined from that review that the leak test was previously accomplished and successfully completed. (1) Put a plug in the strut forward drain outlet (this drain outlet is labeled as ‘‘pylon strut’’). Put an empty container below the strut forward drain outlet to collect water drained through this outlet. (2) Apply 381 to 387 fluid ounces (11.3 to 11.4 liters) of water in 2.5 to 3.5 minutes, to the strut upper spar (strut areas between the forward and mid-vapor barriers). (3) Make sure that no leakage occurred after doing the action specified in paragraph (g)(2) of this AD. (4) Remove the plug from the strut forward drain outlet and make sure that the water is drained through the strut forward drain outlet only. (5) After 3 minutes from accomplishing the action specified in paragraph (g)(4) of this AD, measure the water collected in the container, and do the applicable actions specified in paragraphs (g)(5)(i) through (iii) of this AD. (i) If leaks were found, do corrective action before further flight using a method approved in accordance with the procedures specified in paragraph (h) of this AD. (ii) If no leaks were found and less than 354 fluid ounces (10.5 liters) of water is collected in the container, do corrective action before further flight using a method approved in accordance with the procedures specified in paragraph (h) of this AD. (ii) Before further flight after accomplishing any corrective action required by paragraph (g)(5)(i) or (ii) of this AD, repeat the actions specified in paragraphs (g)(1) through (5) of this AD until successful completion of the test (i.e., no leaks are found and 354 fluid ounces (10.5 liters) of water or more is measured in the container). Note 1 to paragraph (g): Additional guidance for performing the leak (functional) test can be found in Boeing Model 787 Aircraft Maintenance Manual (AMM), 54– 65–01, Strut Spar—Upper—Functional Test. VerDate Sep<11>2014 19:05 Oct 31, 2019 Jkt 250001 (h) 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 (i)(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. (i) Related Information (1) For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3553; email: takahisa.kobayashi@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. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on October 24, 2019. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–23788 Filed 10–31–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0827; Product Identifier 2019–SW–014–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Helicopters Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Notice of proposed rulemaking (NPRM). ACTION: The FAA proposes to supersede Airworthiness Directive (AD) 2011–12–07 for Eurocopter France (now Airbus Helicopters) Model SA–365C, SA–365C1, SA–365C2, SA–365N, SA– 365N1, AS–365N2, AS 365 N3, and SA– 366G1 helicopters. AD 2011–12–07 currently requires repetitively inspecting the adhesive bead between the bushings and the Starflex star (Starflex) arms and the Starflex arm ends. Since the FAA issued AD 2011– 12–07, Airbus Helicopters has developed an improved Starflex. This proposed AD would retain the requirements of AD 2011–12–07 and revise the Applicability paragraph by omitting helicopters with the improved Starflex installed. 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 December 31, 2019. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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– 0827; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the European Aviation Safety Agency (EASA) AD, the economic 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 service information identified in this proposed rule, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641– 0000 or (800) 232–0323; fax (972) 641– 3775; or at http:// www.helicopters.airbus.com/website/ en/ref/Technical-Support_73.html. You E:\FR\FM\01NOP1.SGM 01NOP1

Agencies

[Federal Register Volume 84, Number 212 (Friday, November 1, 2019)]
[Proposed Rules]
[Pages 58636-58638]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-23788]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0719; Product Identifier 2019-NM-137-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 failure of a wing strut leak test due to a 
missing bolt on the firewall. This proposed AD would require a one-time 
leak test of the strut upper spar areas for the left and right wing 
struts, and corrective action if necessary. 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 December 
16, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this 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 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.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0719; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. 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: Tak Kobayashi, Aerospace Engineer, 
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: 206-231-3553; 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-2019-0719; 
Product Identifier 2019-NM-137-AD'' at the beginning of your comments. 
The agency 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 https:/
/

[[Page 58637]]

www.regulations.gov, including any personal information you provide. 
The agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Discussion

    The FAA received a report indicating failure of a wing strut leak 
test due to a missing bolt on the firewall. Failure during manufacture 
to install a bolt that plugs a strut firewall penetration would result 
in a hole in the firewall. This condition, if not addressed, could 
allow flammable fluid leakage in the strut area. This leakage could 
overwhelm the drainage provision, enter the engine compartment, and 
result in an uncontrollable engine fire and consequent structural 
failure of the wing.

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 a one-time leak test of the strut 
upper spar areas for the left and right wing struts, and corrective 
action if necessary.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 2 airplanes of 
U.S. registry. The agency estimates the following costs to comply with 
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255...........................              $0             $255             $510
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition action that would be required based on the results of any 
proposed actions. The FAA has no way of determining the number of 
aircraft that might need this on-condition action:

                 Estimated Costs of On-Condition Action
------------------------------------------------------------------------
                                                             Cost per
           Labor cost                  Parts cost            product
------------------------------------------------------------------------
1 work-hour x $85 per hour =     Minimal...............             $85
 $85.
------------------------------------------------------------------------

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 
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-2019-0719; Product Identifier 
2019-NM-137-AD.

(a) Comments Due Date

    The FAA must receive comments by December 16, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes, 
certificated in any category, line numbers 6, 11, 17, 19, 20, 21, 
23, 25 through 30 inclusive, and 32 through 38 inclusive.

[[Page 58638]]

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

(e) Unsafe Condition

    This AD was prompted by a report of failure of a wing strut leak 
test due to a missing bolt on the firewall. The FAA is issuing this 
AD to address a hole in the firewall, which could allow flammable 
fluid leakage in the strut area. This leakage could overwhelm the 
drainage provision, enter the engine compartment, and result in an 
uncontrollable engine fire and consequent structural failure of the 
wing.

(f) Compliance

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

(g) Leak Test and Corrective Action

    Within 12 months after the effective date of this AD: Do a one-
time leak (functional) test of the strut upper spar areas for the 
left and right wing struts, by doing the actions specified in 
paragraphs (g)(1) through (5) of this AD. A review of airplane 
maintenance records is acceptable in lieu of this test if it can be 
conclusively determined from that review that the leak test was 
previously accomplished and successfully completed.
    (1) Put a plug in the strut forward drain outlet (this drain 
outlet is labeled as ``pylon strut''). Put an empty container below 
the strut forward drain outlet to collect water drained through this 
outlet.
    (2) Apply 381 to 387 fluid ounces (11.3 to 11.4 liters) of water 
in 2.5 to 3.5 minutes, to the strut upper spar (strut areas between 
the forward and mid-vapor barriers).
    (3) Make sure that no leakage occurred after doing the action 
specified in paragraph (g)(2) of this AD.
    (4) Remove the plug from the strut forward drain outlet and make 
sure that the water is drained through the strut forward drain 
outlet only.
    (5) After 3 minutes from accomplishing the action specified in 
paragraph (g)(4) of this AD, measure the water collected in the 
container, and do the applicable actions specified in paragraphs 
(g)(5)(i) through (iii) of this AD.
    (i) If leaks were found, do corrective action before further 
flight using a method approved in accordance with the procedures 
specified in paragraph (h) of this AD.
    (ii) If no leaks were found and less than 354 fluid ounces (10.5 
liters) of water is collected in the container, do corrective action 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (h) of this AD.
    (ii) Before further flight after accomplishing any corrective 
action required by paragraph (g)(5)(i) or (ii) of this AD, repeat 
the actions specified in paragraphs (g)(1) through (5) of this AD 
until successful completion of the test (i.e., no leaks are found 
and 354 fluid ounces (10.5 liters) of water or more is measured in 
the container).

    Note 1 to paragraph (g): Additional guidance for performing the 
leak (functional) test can be found in Boeing Model 787 Aircraft 
Maintenance Manual (AMM), 54-65-01, Strut Spar--Upper--Functional 
Test.

(h) 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 (i)(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.

(i) Related Information

    (1) For more information about this AD, contact Tak Kobayashi, 
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3553; 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. For information on the availability of this 
material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on October 24, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-23788 Filed 10-31-19; 8:45 am]
 BILLING CODE 4910-13-P