Airworthiness Directives; The Boeing Company Airplanes, 24597-24600 [2017-10604]

Download as PDF Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Proposed Rules 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– 2017–0499; Directorate Identifier 2016– NM–205–AD. (a) Comments Due Date We must receive comments by July 14, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Model 747–400, 747–400F, and 747–8F series airplanes, as identified in Boeing Special Attention Service Bulletin 747–25– 3693, dated November 10, 2016. (2) Model 747–8F series airplanes with an original certificate of airworthiness, or an original export certificate of airworthiness, issued after November 10, 2016, and before the effective date of this AD. (3) Model 747–8F series airplanes with an original certificate of airworthiness, or an original export certificate of airworthiness, issued on or after the effective date of this AD. sradovich on DSK3GMQ082PROD with PROPOSALS (d) Subject Air Transport Association (ATA) of America Code 25; Equipment/furnishings. (e) Unsafe Condition This AD was prompted by reports of failure of the fastener assemblies on the crew access ladder handrails. We are issuing this AD to prevent the fastener assemblies from coming loose on the crew access ladder handrails, which could result in serious or fatal injury to personnel. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement For airplanes identified in paragraph (c)(1) of this AD: Within 36 months after the VerDate Sep<11>2014 19:39 May 26, 2017 Jkt 241001 effective date of this AD, replace the fastener assemblies in the crew access ladder handrails with new fastener assemblies, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–25–3693, dated November 10, 2016. (h) Inspection and Replacement (1) For airplanes identified in paragraph (c)(2) of this AD: Within 36 months after the effective date of this AD, do a general visual inspection of the crew access ladder handrails for the discrepant fastener assembly hardware identified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–25– 3693, dated November 10, 2016. A review of airplane maintenance records is acceptable in lieu of this inspection, if the part number(s) of the fastener assembly hardware can be conclusively determined from that review. (2) If any discrepant fastener assembly hardware is found, within 36 months after the effective date of this AD, replace the discrepant fastener assemblies in the crew access ladder handrails with new fastener assemblies, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–25– 3693, dated November 10, 2016. (i) Parts Installation Limitation For airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD: As of the effective date of this AD, no person may install the discrepant fastener hardware identified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–25–3693, dated November 10, 2016, on a crew access ladder on any airplane. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (k)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 24597 Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (k) Related Information (1) For more information about this AD, contact Susan L. Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA; phone: 425–917–6457; fax: 425–917–6590; email: susan.l.monroe@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 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 17, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10606 Filed 5–26–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0500; Directorate Identifier 2017–NM–009–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 MD–11 and MD–11F airplanes. This proposed AD was prompted by fuel system SUMMARY: E:\FR\FM\30MYP1.SGM 30MYP1 24598 Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Proposed Rules reviews conducted by the manufacturer. This proposed AD would require a onetime inspection of the wire assemblies of the tail fuel tank transfer pumps to determine if metallic transitions are installed at the wire harness breakouts, and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 14, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740; telephone 562–797–1717; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0500. sradovich on DSK3GMQ082PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0500; 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: Serj Harutunian, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office VerDate Sep<11>2014 19:39 May 26, 2017 Jkt 241001 (ACO), 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: 562–627–5254; fax: 562–627– 5210; email: serj.harutunian@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–0500; Directorate Identifier 2017–NM–009–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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a final rule titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction, and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements that rule included Amendment 21–78, which established Special Federal Aviation Regulation No. 88 (‘‘SFAR 88’’) at 14 CFR part 21. Subsequently, SFAR 88 was amended by: Amendment 21–82 (67 FR 57490, September 10, 2002; corrected at 67 FR 70809, November 26, 2002) and Amendment 21–83 (67 FR 72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to change ‘‘21–82’’ to ‘‘21–83’’). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, combination of failures, and unacceptable (failure) experience. For all three failure criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. This proposed AD was prompted by fuel system reviews conducted by the manufacturer. In addition, during one event on a Model MD–11 airplane that occurred during flight, a level 1 message ‘‘TAIL L PUMP OFF’’ was annunciated; investigation of the wire bundles in the horizontal stabilizer next to the tail fuel tank revealed burned and broken wires, which showed severe signs of overheating and arcing. This is considered a quality control issue because the type design harnesses were not installed properly during the required SFAR 88 modifications. We are proposing this AD to detect and correct potential ignition sources inside the tail fuel tank, which, in combination with flammable vapors, could result in a fuel tank fire or explosion, and consequent loss of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016. The service information describes procedures for a one-time detailed inspection of the wire assemblies of the tail fuel tank transfer pumps to determine if metallic transitions are installed at the wire harness breakouts, and corrective actions that include repair and replacement of the wire assembly. 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. E:\FR\FM\30MYP1.SGM 30MYP1 24599 Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Proposed Rules Related Rulemaking On May 14, 2010, we issued AD 2010–11–12, Amendment 39–16317 (75 FR 30274, June 1, 2010) (‘‘AD 2010–11– 12’’), for certain Model MD–11 and MD– 11F airplanes. AD 2010–11–12 requires a one-time inspection to determine if metallic transitions are installed on wire harnesses of the tail fuel tank transfer pumps, and to inspect for and repair damaged wires. AD 2010–11–12 also requires repetitive inspections of repaired areas; and a permanent modification of the wire harnesses if metallic transitions are not installed, which would terminate the repetitive inspections. AD 2010–11–12 also requires modifying the case grounding for the alternate fuel pump of the tail fuel tank, the leak detection thermal switch grounding for the number 2 engine, and wire braid grounding in the empennage and number 2 engine inlet. We issued AD 2010–11–12 to prevent insufficient grounding of the fuel pump, which, in combination with an electrical failure within the fuel pump and a compromised electrical bond, could cause a fuel tank ignition, resulting in consequent fire or explosion. On January 3, 2011, we issued AD 2011–02–01, Amendment 39–16574 (76 FR 1983, January 12, 2011) (‘‘AD 2011– 02–01’’), for certain Model MD–11 and MD–11F airplanes. AD 2011–02–01 requires a one-time inspection to detect damage of the wire assemblies of the tail fuel tank fuel system, a wiring change, and corrective actions if necessary. AD 2011–02–01 also requires, for certain airplanes, a general visual inspection for correct installation of the self-adhering high-temperature electrical insulation tape; installation of a wire assembly support bracket and routing wire assembly; changing of certain wire supports; and installation of a wire protection bracket. We issued AD 2011– 02–01 to detect and correct a potential of ignition sources inside fuel tanks, which, in combination with flammable vapors, could result in a fuel tank fire or explosion, and consequent loss of the airplane. This proposed AD would not supersede or terminate the actions required by AD 2010–11–12 and AD 2011–02–01. Certain airplanes identified in the related rulemaking may not have the correct wire harness with metallic transitions installed; therefore this proposed AD would address the unsafe condition on those airplanes. 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. The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ are actions that 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 110 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ................................ 4 work-hours × $85 per hour = $340 ..................................... We estimate the following costs to do any necessary repairs/replacements that would be required based on the results Cost per product Parts cost of the proposed inspection. We have no way of determining the number of $0 $340 Cost on U.S. operators $37,400 aircraft that might need these repairs/ replacements: ON-CONDITION COSTS Action Labor cost Repair .............................................. Replacement .................................... 9 work-hours × $85 per hour = $765 ........................................................ 16 work-hours × $85 per hour = $1,360 ................................................... sradovich on DSK3GMQ082PROD 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. 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 VerDate Sep<11>2014 19:39 May 26, 2017 Jkt 241001 Parts cost 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 PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 $0 57,526 Cost per product $765 58,886 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 E:\FR\FM\30MYP1.SGM 30MYP1 24600 Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Proposed Rules 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– 2017–0500; Directorate Identifier 2017– NM–009–AD. (a) Comments Due Date We must receive comments by July 14, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Boeing Company Model MD–11 and MD–11F airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016. (d) Subject Air Transport Association (ATA) of America Code 28; Fuel. (e) Unsafe Condition This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to detect and correct potential ignition sources inside the tail fuel tank, which, in combination with flammable vapors, could result in a fuel tank fire or explosion, and consequent loss of the airplane. sradovich on DSK3GMQ082PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) One-Time Inspection and Corrective Actions Within 27 months after the effective date of this AD: Do a one-time detailed inspection of the wire assemblies of the tail fuel tank transfer pumps to determine if metallic transitions are installed at the wire harness breakouts, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016. If metallic transitions are installed, no further action is required by this VerDate Sep<11>2014 19:39 May 26, 2017 Jkt 241001 paragraph. If metallic transitions are not installed, do the corrective actions required by paragraphs (g)(1) and (g)(2) of this AD, as applicable, except as required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) Repair any affected wire assembly before further flight, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016, or replace any affected wire assembly with a new assembly before further flight, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016. If the replacement is done, no further action is required for that wire assembly only. (2) Within 24 months after accomplishment of the repair required by paragraph (g)(1) of this AD: Replace any repaired wire assembly with a new assembly, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016. (h) Service Information Exceptions (1) Where Part 4.1.f. of the Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016, specifies ‘‘CONTROLLER FUEL SYSTEM—ADJUSTMENT/TEST refer to MD–11, AMM (Airplane Maintenance Manual) 28–28–01 as an accepted procedure’’: Adjust and test the controller fuel system. If the test fails do corrective actions, repeat the test, and do applicable corrective actions until the system passes the test. (2) Where Part 4.1.g. of the Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016, specifies ‘‘OPERATIONAL TEST OF THE FILL SHUTOFF VALVE CONTROLLER refer to MD–11 AMM 26–21— 02, as an accepted procedure’’: Do the operational test of the part. If the part fails the test, do corrective actions, repeat the test, and do applicable corrective actions until the part passes the test. (3) Where Part 4.1.h. of the Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A150, dated October 6, 2016, specifies ‘‘SWITCH, PUMP LOW PRESSURE—ADJUSTMENT/TEST, refer to MD–11 AMM 28–44–01, as an accepted procedure’’: Do the operational test of the part. If the part fails the test, do corrective actions, repeat the test, and do applicable corrective actions until the part passes the test. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (j)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. PO 00000 Frm 00031 Fmt 4702 Sfmt 9990 (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, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, ´ contact Serj Harutunian, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: 562–627–5254; fax: 562–627–5210; email: serj.harutunian@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; telephone 562–797–1717; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on May 17, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10604 Filed 5–26–17; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\30MYP1.SGM 30MYP1

Agencies

[Federal Register Volume 82, Number 102 (Tuesday, May 30, 2017)]
[Proposed Rules]
[Pages 24597-24600]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10604]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0500; Directorate Identifier 2017-NM-009-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 MD-11 and MD-11F airplanes. This 
proposed AD was prompted by fuel system

[[Page 24598]]

reviews conducted by the manufacturer. This proposed AD would require a 
one-time inspection of the wire assemblies of the tail fuel tank 
transfer pumps to determine if metallic transitions are installed at 
the wire harness breakouts, and corrective actions if necessary. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 14, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 
562-797-1717; Internet https://www.myboeingfleet.com. You may view this 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the 
availability of this material at the FAA, call 425-227-1221. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0500.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0500; 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: S[eacute]rj Harutunian, Aerospace 
Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, 
California 90712-4137; phone: 562-627-5254; fax: 562-627-5210; email: 
serj.harutunian@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0500; 
Directorate Identifier 2017-NM-009-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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a final 
rule titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction, and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements that rule 
included Amendment 21-78, which established Special Federal Aviation 
Regulation No. 88 (``SFAR 88'') at 14 CFR part 21. Subsequently, SFAR 
88 was amended by: Amendment 21-82 (67 FR 57490, September 10, 2002; 
corrected at 67 FR 70809, November 26, 2002) and Amendment 21-83 (67 FR 
72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to 
change ``21-82'' to ``21-83'').
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: Single failures, combination of 
failures, and unacceptable (failure) experience. For all three failure 
criteria, the evaluations included consideration of previous actions 
taken that may mitigate the need for further action.
    This proposed AD was prompted by fuel system reviews conducted by 
the manufacturer. In addition, during one event on a Model MD-11 
airplane that occurred during flight, a level 1 message ``TAIL L PUMP 
OFF'' was annunciated; investigation of the wire bundles in the 
horizontal stabilizer next to the tail fuel tank revealed burned and 
broken wires, which showed severe signs of overheating and arcing. This 
is considered a quality control issue because the type design harnesses 
were not installed properly during the required SFAR 88 modifications.
    We are proposing this AD to detect and correct potential ignition 
sources inside the tail fuel tank, which, in combination with flammable 
vapors, could result in a fuel tank fire or explosion, and consequent 
loss of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin MD11-28A150, dated 
October 6, 2016. The service information describes procedures for a 
one-time detailed inspection of the wire assemblies of the tail fuel 
tank transfer pumps to determine if metallic transitions are installed 
at the wire harness breakouts, and corrective actions that include 
repair and replacement of the wire assembly. 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.

[[Page 24599]]

Related Rulemaking

    On May 14, 2010, we issued AD 2010-11-12, Amendment 39-16317 (75 FR 
30274, June 1, 2010) (``AD 2010-11-12''), for certain Model MD-11 and 
MD-11F airplanes. AD 2010-11-12 requires a one-time inspection to 
determine if metallic transitions are installed on wire harnesses of 
the tail fuel tank transfer pumps, and to inspect for and repair 
damaged wires. AD 2010-11-12 also requires repetitive inspections of 
repaired areas; and a permanent modification of the wire harnesses if 
metallic transitions are not installed, which would terminate the 
repetitive inspections. AD 2010-11-12 also requires modifying the case 
grounding for the alternate fuel pump of the tail fuel tank, the leak 
detection thermal switch grounding for the number 2 engine, and wire 
braid grounding in the empennage and number 2 engine inlet. We issued 
AD 2010-11-12 to prevent insufficient grounding of the fuel pump, 
which, in combination with an electrical failure within the fuel pump 
and a compromised electrical bond, could cause a fuel tank ignition, 
resulting in consequent fire or explosion.
    On January 3, 2011, we issued AD 2011-02-01, Amendment 39-16574 (76 
FR 1983, January 12, 2011) (``AD 2011-02-01''), for certain Model MD-11 
and MD-11F airplanes. AD 2011-02-01 requires a one-time inspection to 
detect damage of the wire assemblies of the tail fuel tank fuel system, 
a wiring change, and corrective actions if necessary. AD 2011-02-01 
also requires, for certain airplanes, a general visual inspection for 
correct installation of the self-adhering high-temperature electrical 
insulation tape; installation of a wire assembly support bracket and 
routing wire assembly; changing of certain wire supports; and 
installation of a wire protection bracket. We issued AD 2011-02-01 to 
detect and correct a potential of ignition sources inside fuel tanks, 
which, in combination with flammable vapors, could result in a fuel 
tank fire or explosion, and consequent loss of the airplane.
    This proposed AD would not supersede or terminate the actions 
required by AD 2010-11-12 and AD 2011-02-01. Certain airplanes 
identified in the related rulemaking may not have the correct wire 
harness with metallic transitions installed; therefore this proposed AD 
would address the unsafe condition on those airplanes.

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.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that 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 110 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
----------------------------------------------------------------------------------------------------------------
Inspection.........................  4 work-hours x $85 per hour              $0            $340         $37,400
                                      = $340.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the 
proposed inspection. We have no way of determining the number of 
aircraft that might need these repairs/replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair.....................................  9 work-hours x $85 per hour = $765.              $0            $765
Replacement................................  16 work-hours x $85 per hour =               57,526          58,886
                                              $1,360.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

[[Page 24600]]

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-2017-0500; Directorate Identifier 
2017-NM-009-AD.

(a) Comments Due Date

    We must receive comments by July 14, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Boeing Company Model MD-11 and MD-11F 
airplanes, certificated in any category, as identified in Boeing 
Alert Service Bulletin MD11-28A150, dated October 6, 2016.

(d) Subject

    Air Transport Association (ATA) of America Code 28; Fuel.

(e) Unsafe Condition

    This AD was prompted by fuel system reviews conducted by the 
manufacturer. We are issuing this AD to detect and correct potential 
ignition sources inside the tail fuel tank, which, in combination 
with flammable vapors, could result in a fuel tank fire or 
explosion, and consequent loss of the airplane.

(f) Compliance

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

(g) One-Time Inspection and Corrective Actions

    Within 27 months after the effective date of this AD: Do a one-
time detailed inspection of the wire assemblies of the tail fuel 
tank transfer pumps to determine if metallic transitions are 
installed at the wire harness breakouts, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin MD11-
28A150, dated October 6, 2016. If metallic transitions are 
installed, no further action is required by this paragraph. If 
metallic transitions are not installed, do the corrective actions 
required by paragraphs (g)(1) and (g)(2) of this AD, as applicable, 
except as required by paragraphs (h)(1), (h)(2), and (h)(3) of this 
AD.
    (1) Repair any affected wire assembly before further flight, in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin MD11-28A150, dated October 6, 2016, or 
replace any affected wire assembly with a new assembly before 
further flight, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin MD11-28A150, dated 
October 6, 2016. If the replacement is done, no further action is 
required for that wire assembly only.
    (2) Within 24 months after accomplishment of the repair required 
by paragraph (g)(1) of this AD: Replace any repaired wire assembly 
with a new assembly, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin MD11-28A150, dated 
October 6, 2016.

(h) Service Information Exceptions

    (1) Where Part 4.1.f. of the Accomplishment Instructions of 
Boeing Alert Service Bulletin MD11-28A150, dated October 6, 2016, 
specifies ``CONTROLLER FUEL SYSTEM--ADJUSTMENT/TEST refer to MD-11, 
AMM (Airplane Maintenance Manual) 28-28-01 as an accepted 
procedure'': Adjust and test the controller fuel system. If the test 
fails do corrective actions, repeat the test, and do applicable 
corrective actions until the system passes the test.
    (2) Where Part 4.1.g. of the Accomplishment Instructions of 
Boeing Alert Service Bulletin MD11-28A150, dated October 6, 2016, 
specifies ``OPERATIONAL TEST OF THE FILL SHUTOFF VALVE CONTROLLER 
refer to MD-11 AMM 26-21--02, as an accepted procedure'': Do the 
operational test of the part. If the part fails the test, do 
corrective actions, repeat the test, and do applicable corrective 
actions until the part passes the test.
    (3) Where Part 4.1.h. of the Accomplishment Instructions of 
Boeing Alert Service Bulletin MD11-28A150, dated October 6, 2016, 
specifies ``SWITCH, PUMP LOW PRESSURE--ADJUSTMENT/TEST, refer to MD-
11 AMM 28-44-01, as an accepted procedure'': Do the operational test 
of the part. If the part fails the test, do corrective actions, 
repeat the test, and do applicable corrective actions until the part 
passes the test.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (j)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-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, Los Angeles ACO, to make those findings. To be approved, 
the repair method, modification deviation, or alteration deviation 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(i)(4)(i) and (i)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(j) Related Information

    (1) For more information about this AD, contact S[eacute]rj 
Harutunian, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, 
Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; phone: 562-627-5254; fax: 562-627-5210; email: 
serj.harutunian@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; 
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You 
may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.


    Issued in Renton, Washington, on May 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10604 Filed 5-26-17; 8:45 am]
 BILLING CODE 4910-13-P