Airworthiness Directives; The Boeing Company Airplanes, 20408-20411 [2020-07645]

Download as PDF 20408 Federal Register / Vol. 85, No. 71 / Monday, April 13, 2020 / Rules and Regulations (n) Related Information For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3226; email tom.rodriguez@faa.gov. (o) Material Incorporated by Reference khammond on DSKJM1Z7X2PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on May 18, 2020. (i) European Union Aviation Safety Agency (EASA) AD 2019–0257, dated October 17, 2019. (ii) [Reserved] (4) The following service information was approved for IBR on April 2, 2019 (84 FR 6059, February 26, 2019). (i) Chapter 5–40–00, Airworthiness Limitations, DGT 107838, Revision 7, dated August 24, 2018, of the Dassault Falcon 7X Maintenance Manual (MM). (ii) [Reserved] (5) For information about EASA AD 2019– 0257, 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. (6) For Dassault Aviation service information identified in this AD, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; internet https://www.dassaultfalcon.com. (7) 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 https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0991. (8) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Issued on April 3, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–07646 Filed 4–10–20; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 17:15 Apr 10, 2020 Jkt 250001 DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0859; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. 14 CFR Part 39 [Docket No. FAA–2019–0859; Product Identifier 2019–NM–114–AD; Amendment 39–19893; AD 2020–07–14] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer indicating that the existing bond path design provides insufficient bond resistance margin between the fuel pump motor/impeller and structure. This AD requires replacement of the bonding jumpers on the auxiliary power unit (APU) fuel pump. This AD also requires, for certain airplanes, installation of a second bonding jumper; an inspection of the override/jettison fuel pumps and transfer/jettison fuel pumps to determine if the bonding jumper has a one-piece braid or twopiece braid and replacement of the bonding jumper if necessary; and replacement of the bonding jumper on the electrical scavenge fuel pump. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 18, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 18, 2020. ADDRESSES: For service information identified in this final rule, 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0859. SUMMARY: PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: Jeffrey Rothman, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206– 231–3558; email: jeffrey.rothman@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747– 400F, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on November 8, 2019 (84 FR 60351). The NPRM was prompted by fuel system reviews conducted by the manufacturer indicating that the existing bond path design provides insufficient bond resistance margin between the fuel pump motor/impeller and structure. The NPRM proposed to require replacement of the bonding jumpers on the APU fuel pump. The NPRM also proposed to require, for certain airplanes, installation of a second bonding jumper; an inspection of the override/jettison fuel pumps and transfer/jettison fuel pumps to determine if the bonding jumper has a one-piece braid or two-piece braid and replacement of the bonding jumper if necessary; and replacement of the bonding jumper on the electrical scavenge fuel pump. Comments The FAA gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. E:\FR\FM\13APR1.SGM 13APR1 20409 Federal Register / Vol. 85, No. 71 / Monday, April 13, 2020 / Rules and Regulations Support for the NPRM The Air Line Pilots Association, International (ALPA) and Boeing indicated support for the NPRM. An anonymous commenter also indicated support for the NPRM. Two other commenters, Patrick Imperatrice and Gaganjyot Arora, stated that they supported the NPRM. Request To Clarify Requirements for Certain Airplanes Lufthansa Technik AG on behalf of Lufthansa German Airlines requested that the FAA add a note to the proposed AD to clarify the requirements for airplanes on which BMS 10–20 was not used while accomplishing Boeing Service Bulletin 747–28–2228, dated November 4, 1999 (Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001, is referred to as the appropriate source of service information for accomplishing the proposed actions.). Lufthansa Technik AG asked that the FAA consider whether an airplane on which Boeing Service Bulletin 747–28–2228, dated November 4, 1999, was accomplished without using BMS 10–20 is in compliance with the proposed AD. The FAA agrees to clarify the requirements. Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001, specifies it is necessary to rebond the bonding jumper if BMS 10–20 was applied on the mating surfaces between the bonding jumper and rear spar while accomplishing Boeing Service Bulletin 747–28–2228, dated November 4, 1999. However, Boeing Service Bulletin 747–28–2228, dated November 4, 1999, specifies limits to the bonding resistance values between the pump housing and rear spar structure. Complying with those bonding resistance values is required to address the unsafe condition, regardless of whether or not BMS 10–20 was applied. These bonding resistance limits were unchanged between Boeing Service Bulletin 747–28–2228, dated November 4, 1999, and Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001. Therefore, credit can be given if it can be conclusively determined that all bonding resistance limits specified in Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001, have been met. The FAA has added paragraph (i) to this AD to provide this credit and reidentified subsequent paragraphs accordingly. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. The FAA also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 The FAA reviewed Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001. This service information describes procedures for a replacement of the bonding jumpers on the APU fuel pump; an inspection of the six override/jettison fuel pumps and of the two transfer/jettison fuel pumps to determine if the bonding jumper has a one-piece braid or two-piece braid, and replacement of the existing bonding jumper if the bonding jumper has a onepiece braid; installation of a second bonding jumper; and replacement of the bonding jumper on the electrical scavenge fuel pump. 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. Other Relevant Rulemaking Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001, identifies ‘‘Boeing Service Bulletin 747– 28–2033’’ as a concurrent requirement for certain airplanes. Boeing Alert Service Bulletin 747–28A2033, Revision 1, dated December 18, 2003, is the appropriate source of service information for accomplishing the installation required by AD 2005–01–07, Amendment 39–13931 (70 FR 1336, January 7, 2005) (‘‘AD 2005–01–07’’). The compliance time for accomplishing the installation required by AD 2005– 01–07 has already passed; therefore, it is not necessary to include Boeing Alert Service Bulletin 747–28A2033 as a concurrent requirement in this AD. The FAA issued AD 2005–01–07 to ensure adequate electrical bonding between the housing of each fuel pump and airplane structure outside the fuel tanks. Inadequate electrical bonding, in the event of a lightning strike or fuel pump electrical fault, could cause electrical arcing and ignition of fuel vapor in the wing fuel tank, which could result in a fuel tank explosion. Costs of Compliance The FAA estimates that this AD affects 74 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Replacement, Installation, and Inspection. Up to 15 work-hours × $85 per hour = Up to $1,275. Up to $2,000 ......... Up to $3,275 ......... khammond on DSKJM1Z7X2PROD with RULES The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. The FAA has no way of determining the Cost on U.S. operators Up to $242,350. number of aircraft that might need these replacements: ON-CONDITION COSTS Cost per product Action Labor cost Parts cost Replacement .................................. Up to 6 work-hours × $85 per hour = Up to $510. Up to $950 .................................... VerDate Sep<11>2014 17:15 Apr 10, 2020 Jkt 250001 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM Up to $1,460. 13APR1 20410 Federal Register / Vol. 85, No. 71 / Monday, April 13, 2020 / Rules and Regulations 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. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: (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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: khammond on DSKJM1Z7X2PROD with RULES 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): ■ VerDate Sep<11>2014 17:15 Apr 10, 2020 Jkt 250001 2020–07–14 The Boeing Company: Amendment 39–19893; Docket No. FAA–2019–0859; Product Identifier 2019–NM–114–AD. (a) Effective Date This AD is effective May 18, 2020. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, line numbers (L/Ns) 1 through 1229 inclusive. (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 indicating that the existing bond path design provides insufficient bond resistance margin between the fuel pump motor/impeller and structure. The FAA is issuing this AD to address insufficient bond resistance margin between the fuel pump motor/impeller and structure. In the event of a fuel pump electrical fault, this condition might cause arcs at the existing fuel pump/tank interfaces and an ignition of fuel vapor in the wing fuel tank, which could result in a fuel tank explosion and consequent loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions The definitions specified in paragraphs (g)(1) through (4) of this AD apply. (1) Group 1 airplanes: L/Ns 1 through 167 inclusive. (2) Group 2 airplanes: L/Ns 168 through 971 inclusive. (3) Group 3 airplanes: L/Ns 972 through 1161 inclusive. (4) Group 4 airplanes: L/Ns 1162 through 1229 inclusive. (h) Replacement, Installation, and Inspection Within 60 months after the effective date of this AD, do the applicable actions specified in paragraphs (h)(1) through (4) of this AD, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001. (1) For Groups 1, 2, and 3 airplanes: Do the actions specified in paragraphs (h)(1)(i) and (ii) of this AD. (i) Do a general visual inspection of the six override/jettison fuel pumps to determine if the bonding jumper has a one-piece braid or two-piece braid. If the bonding jumper has a one-piece braid, within 60 months after the effective date of this AD, replace the existing bonding jumper. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 (ii) Install a second bonding jumper. (2) For Groups 1, 2, and 3 airplanes with horizontal stabilizer fuel tanks: Do the actions specified in paragraphs (h)(2)(i) and (ii) of this AD. (i) Do a general visual inspection of the two transfer/jettison fuel pumps to determine if the bonding jumper has a one-piece braid or a two-piece braid. If the bonding jumper has a one-piece braid, within 60 months after the effective date of this AD, replace the existing bonding jumper. (ii) Install a second bonding jumper. (3) For all airplanes: Replace the bonding jumpers on the auxiliary power unit (APU) fuel pump. (4) For Groups 1 and 2 airplanes: Replace the bonding jumper on the electrical scavenge fuel pump. (i) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747–28–2228, dated November 4, 1999, provided it can conclusively be determined that all bonding resistance values specified in Boeing Service Bulletin 747–28– 2228, Revision 1, dated September 27, 2001, have been met. (j) 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 (k) of this AD. Information may be emailed to: 9-ANMSeattle-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. (k) Related Information For more information about this AD, contact Jeffrey Rothman, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3558; email: jeffrey.rothman@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this E:\FR\FM\13APR1.SGM 13APR1 Federal Register / Vol. 85, No. 71 / Monday, April 13, 2020 / Rules and Regulations paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Service Bulletin 747–28–2228, Revision 1, dated September 27, 2001. (ii) [Reserved] (3) 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. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on April 3, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2020–07645 Filed 4–10–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0985; Product Identifier 2019–NM–183–AD; Amendment 39–19891; AD 2020–07–12] RIN 2120–AA64 Airworthiness Directives; ATR—GIE Avions de Transport Re´gional Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain ATR—GIE Avions de Transport Re´gional Model ATR42–500 airplanes. This AD was prompted by a report of interference between bonding braid screws and pitch tab control rods on the ATR final assembly line. This AD requires an inspection of the bonding braid screws for proper installation, a detailed inspection for damage to the pitch tab control rods if necessary, and replacement of the pitch tab control rods if necessary, as specified in a European Union Aviation Safety Agency khammond on DSKJM1Z7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 17:15 Apr 10, 2020 Jkt 250001 (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 18, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 18, 2020. ADDRESSES: For the material incorporated by reference (IBR) in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR 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. It is also available in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0985. You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0985; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3220. SUPPLEMENTARY INFORMATION: Discussion The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2019–0262, dated October 22, 2019 (‘‘EASA AD 2019–0262’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain ATR—GIE Avions de Transport Re´gional Model ATR42–500 airplanes. PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 20411 The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain ATR—GIE Avions de Transport Re´gional Model ATR42–500 airplanes. The NPRM published in the Federal Register on December 19, 2019 (84 FR 69662). The NPRM was prompted by a report of interference between bonding braid screws and pitch tab control rods on the ATR final assembly line. The NPRM proposed to require an inspection of the bonding braid screws for proper installation, a detailed inspection for damage to the pitch tab control rods if necessary, and replacement of the pitch tab control rods if necessary. The FAA is issuing this AD to address interference between bonding braid screws and pitch tab control rods, which could lead to failure of the rods and tab disconnection, possibly resulting in reduced control of the airplane. See the MCAI for additional background information. Comments The FAA gave the public the opportunity to participate in developing this final rule. The following presents the comment received on the NPRM and the FAA’s response to the comment. Request To Allow Credit for Work Done Using Alternative Service Information Silver Airways requested credit for accomplishment of the proposed requirements on its current fleet of affected ATR42 airplanes using alternative service information, i.e., by accomplishment of ATR All Operator Message (AOM) 2019/09, Issue 2, and compliance with ATR Service Bulletin ATR42–27–0112, dated August 6, 2019, referencing EASA AD 2019–0262. The FAA disagrees with the request because the commenter provided no justification. The FAA has determined that in order to address the identified unsafe condition, operators must comply with the requirements of EASA AD 2019–0262, except as specified in paragraph (h) of this AD. EASA AD 2019–0262 specifies only ATR Service Bulletin ATR42–27–0112 for compliance actions, and it does not specify an AOM. However, under the provisions of paragraph (j) of this AD, the FAA will consider requests for approval to use alternative service information if sufficient data are submitted to substantiate that the actions specified in the alternative service information would provide an acceptable level of safety. The FAA has not changed this AD with regard to this request. E:\FR\FM\13APR1.SGM 13APR1

Agencies

[Federal Register Volume 85, Number 71 (Monday, April 13, 2020)]
[Rules and Regulations]
[Pages 20408-20411]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-07645]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0859; Product Identifier 2019-NM-114-AD; Amendment 
39-19893; AD 2020-07-14]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-
200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, 
and 747SP series airplanes. This AD was prompted by fuel system reviews 
conducted by the manufacturer indicating that the existing bond path 
design provides insufficient bond resistance margin between the fuel 
pump motor/impeller and structure. This AD requires replacement of the 
bonding jumpers on the auxiliary power unit (APU) fuel pump. This AD 
also requires, for certain airplanes, installation of a second bonding 
jumper; an inspection of the override/jettison fuel pumps and transfer/
jettison fuel pumps to determine if the bonding jumper has a one-piece 
braid or two-piece braid and replacement of the bonding jumper if 
necessary; and replacement of the bonding jumper on the electrical 
scavenge fuel pump. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective May 18, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 18, 
2020.

ADDRESSES: For service information identified in this final rule, 
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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0859.

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-
0859; 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 final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations is U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Jeffrey Rothman, Aerospace Engineer, 
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: 206-231-3558; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain The Boeing 
Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series 
airplanes. The NPRM published in the Federal Register on November 8, 
2019 (84 FR 60351). The NPRM was prompted by fuel system reviews 
conducted by the manufacturer indicating that the existing bond path 
design provides insufficient bond resistance margin between the fuel 
pump motor/impeller and structure. The NPRM proposed to require 
replacement of the bonding jumpers on the APU fuel pump. The NPRM also 
proposed to require, for certain airplanes, installation of a second 
bonding jumper; an inspection of the override/jettison fuel pumps and 
transfer/jettison fuel pumps to determine if the bonding jumper has a 
one-piece braid or two-piece braid and replacement of the bonding 
jumper if necessary; and replacement of the bonding jumper on the 
electrical scavenge fuel pump.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The following presents the comments 
received on the NPRM and the FAA's response to each comment.

[[Page 20409]]

Support for the NPRM

    The Air Line Pilots Association, International (ALPA) and Boeing 
indicated support for the NPRM. An anonymous commenter also indicated 
support for the NPRM. Two other commenters, Patrick Imperatrice and 
Gaganjyot Arora, stated that they supported the NPRM.

Request To Clarify Requirements for Certain Airplanes

    Lufthansa Technik AG on behalf of Lufthansa German Airlines 
requested that the FAA add a note to the proposed AD to clarify the 
requirements for airplanes on which BMS 10-20 was not used while 
accomplishing Boeing Service Bulletin 747-28-2228, dated November 4, 
1999 (Boeing Service Bulletin 747-28-2228, Revision 1, dated September 
27, 2001, is referred to as the appropriate source of service 
information for accomplishing the proposed actions.). Lufthansa Technik 
AG asked that the FAA consider whether an airplane on which Boeing 
Service Bulletin 747-28-2228, dated November 4, 1999, was accomplished 
without using BMS 10-20 is in compliance with the proposed AD.
    The FAA agrees to clarify the requirements. Boeing Service Bulletin 
747-28-2228, Revision 1, dated September 27, 2001, specifies it is 
necessary to rebond the bonding jumper if BMS 10-20 was applied on the 
mating surfaces between the bonding jumper and rear spar while 
accomplishing Boeing Service Bulletin 747-28-2228, dated November 4, 
1999. However, Boeing Service Bulletin 747-28-2228, dated November 4, 
1999, specifies limits to the bonding resistance values between the 
pump housing and rear spar structure. Complying with those bonding 
resistance values is required to address the unsafe condition, 
regardless of whether or not BMS 10-20 was applied. These bonding 
resistance limits were unchanged between Boeing Service Bulletin 747-
28-2228, dated November 4, 1999, and Boeing Service Bulletin 747-28-
2228, Revision 1, dated September 27, 2001. Therefore, credit can be 
given if it can be conclusively determined that all bonding resistance 
limits specified in Boeing Service Bulletin 747-28-2228, Revision 1, 
dated September 27, 2001, have been met. The FAA has added paragraph 
(i) to this AD to provide this credit and reidentified subsequent 
paragraphs accordingly.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety and the public interest 
require adopting this final rule with the changes described previously 
and minor editorial changes. The FAA has determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    The FAA also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Service Bulletin 747-28-2228, Revision 1, 
dated September 27, 2001. This service information describes procedures 
for a replacement of the bonding jumpers on the APU fuel pump; an 
inspection of the six override/jettison fuel pumps and of the two 
transfer/jettison fuel pumps to determine if the bonding jumper has a 
one-piece braid or two-piece braid, and replacement of the existing 
bonding jumper if the bonding jumper has a one-piece braid; 
installation of a second bonding jumper; and replacement of the bonding 
jumper on the electrical scavenge fuel pump. 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.

Other Relevant Rulemaking

    Boeing Service Bulletin 747-28-2228, Revision 1, dated September 
27, 2001, identifies ``Boeing Service Bulletin 747-28-2033'' as a 
concurrent requirement for certain airplanes. Boeing Alert Service 
Bulletin 747-28A2033, Revision 1, dated December 18, 2003, is the 
appropriate source of service information for accomplishing the 
installation required by AD 2005-01-07, Amendment 39-13931 (70 FR 1336, 
January 7, 2005) (``AD 2005-01-07''). The compliance time for 
accomplishing the installation required by AD 2005-01-07 has already 
passed; therefore, it is not necessary to include Boeing Alert Service 
Bulletin 747-28A2033 as a concurrent requirement in this AD. The FAA 
issued AD 2005-01-07 to ensure adequate electrical bonding between the 
housing of each fuel pump and airplane structure outside the fuel 
tanks. Inadequate electrical bonding, in the event of a lightning 
strike or fuel pump electrical fault, could cause electrical arcing and 
ignition of fuel vapor in the wing fuel tank, which could result in a 
fuel tank explosion.

Costs of Compliance

    The FAA estimates that this AD affects 74 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Replacement, Installation, and    Up to 15 work-      Up to $2,000......  Up to $3,275......  Up to $242,350.
 Inspection.                       hours x $85 per
                                   hour = Up to
                                   $1,275.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
proposed inspection. The FAA has no way of determining the number of 
aircraft that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement..........................  Up to 6 work-hours x     Up to $950.............  Up to $1,460.
                                        $85 per hour = Up to
                                        $510.
----------------------------------------------------------------------------------------------------------------


[[Page 20410]]

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.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2020-07-14 The Boeing Company: Amendment 39-19893; Docket No. FAA-
2019-0859; Product Identifier 2019-NM-114-AD.

(a) Effective Date

    This AD is effective May 18, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes, certificated in 
any category, line numbers (L/Ns) 1 through 1229 inclusive.

(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 indicating that the existing bond path design provides 
insufficient bond resistance margin between the fuel pump motor/
impeller and structure. The FAA is issuing this AD to address 
insufficient bond resistance margin between the fuel pump motor/
impeller and structure. In the event of a fuel pump electrical 
fault, this condition might cause arcs at the existing fuel pump/
tank interfaces and an ignition of fuel vapor in the wing fuel tank, 
which could result in a fuel tank explosion and consequent loss of 
the airplane.

(f) Compliance

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

(g) Definitions

    The definitions specified in paragraphs (g)(1) through (4) of 
this AD apply.
    (1) Group 1 airplanes: L/Ns 1 through 167 inclusive.
    (2) Group 2 airplanes: L/Ns 168 through 971 inclusive.
    (3) Group 3 airplanes: L/Ns 972 through 1161 inclusive.
    (4) Group 4 airplanes: L/Ns 1162 through 1229 inclusive.

(h) Replacement, Installation, and Inspection

    Within 60 months after the effective date of this AD, do the 
applicable actions specified in paragraphs (h)(1) through (4) of 
this AD, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 747-28-2228, Revision 1, dated September 27, 
2001.
    (1) For Groups 1, 2, and 3 airplanes: Do the actions specified 
in paragraphs (h)(1)(i) and (ii) of this AD.
    (i) Do a general visual inspection of the six override/jettison 
fuel pumps to determine if the bonding jumper has a one-piece braid 
or two-piece braid. If the bonding jumper has a one-piece braid, 
within 60 months after the effective date of this AD, replace the 
existing bonding jumper.
    (ii) Install a second bonding jumper.
    (2) For Groups 1, 2, and 3 airplanes with horizontal stabilizer 
fuel tanks: Do the actions specified in paragraphs (h)(2)(i) and 
(ii) of this AD.
    (i) Do a general visual inspection of the two transfer/jettison 
fuel pumps to determine if the bonding jumper has a one-piece braid 
or a two-piece braid. If the bonding jumper has a one-piece braid, 
within 60 months after the effective date of this AD, replace the 
existing bonding jumper.
    (ii) Install a second bonding jumper.
    (3) For all airplanes: Replace the bonding jumpers on the 
auxiliary power unit (APU) fuel pump.
    (4) For Groups 1 and 2 airplanes: Replace the bonding jumper on 
the electrical scavenge fuel pump.

(i) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Service Bulletin 747-28-2228, 
dated November 4, 1999, provided it can conclusively be determined 
that all bonding resistance values specified in Boeing Service 
Bulletin 747-28-2228, Revision 1, dated September 27, 2001, have 
been met.

(j) 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 (k) 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.

(k) Related Information

    For more information about this AD, contact Jeffrey Rothman, 
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3558; email: [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this

[[Page 20411]]

paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Service Bulletin 747-28-2228, Revision 1, dated 
September 27, 2001.
    (ii) [Reserved]
    (3) 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on April 3, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-07645 Filed 4-10-20; 8:45 am]
 BILLING CODE 4910-13-P
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