Airworthiness Directives; The Boeing Company Airplanes, 22915-22918 [2017-10033]

Download as PDF Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ 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): ■ Bombardier, Inc.: Docket No. FAA–2017– 0481; Directorate Identifier 2016–NM– 196–AD. (a) Comments Due Date We must receive comments by July 3, 2017. sradovich on DSK3GMQ082PROD with PROPOSALS (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., Model BD–100–1A10 airplanes, certificated in any category, serial numbers 20003 through 20635 inclusive. (d) Subject Air Transport Association (ATA) of America Code 24, Electrical power. VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 (e) Reason This AD was prompted by reports of low clearance in the aft equipment bay between auxiliary power unit (APU) generator power cables and a hydraulic line, which can cause damage to wire insulation. We are issuing this AD to prevent electrical arcing from power cables, which could cause a fire in the aft equipment bay. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of APU Generator Power Cables and Hydraulic Line, Repairs, and Modification Within 24 months after the effective date of this AD, do the applicable actions required by paragraph (g)(1) or (g)(2) of this AD. (1) For airplanes having serial numbers 20003 through 20500 inclusive: Do a general visual inspection of the APU generator power cables and the adjacent hydraulic line for damage, and do all applicable repairs; and modify the APU generator power cable installation; in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–24–28, dated July 27, 2016, except as required by paragraph (h) of this AD. Do all applicable repairs before further flight. (2) For airplanes having serial numbers 20501 through 20635 inclusive: Do a general visual inspection of the APU generator power cables and the adjacent hydraulic line for damage, and do all applicable repairs; and modify the APU generator power cable installation; in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 350–24–003, dated July 27, 2016, except as required by paragraph (h) of this AD. Do all applicable repairs before further flight. (h) Exception to the Service Information Where Bombardier Service Bulletin 100– 24–28, dated July 27, 2016, and Bombardier Service Bulletin 350–24–003, dated July 27, 2016, specify to contact the manufacturer for repair, before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO, ANE–170, 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 ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 22915 your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2016–28, dated September 28, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0481. (2) For more information about this AD, contact Assata Dessaline, Aerospace Engineer, Avionics and Services Branch, ANE–172, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7301; fax 516–794–5531. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this 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 12, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10133 Filed 5–18–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0340; Directorate Identifier 2017–NM–002–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 757–200, –200PF, and –300 series airplanes. This proposed AD was prompted by reports SUMMARY: E:\FR\FM\19MYP1.SGM 19MYP1 22916 Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules of cracking found at a certain fuselage frame inner chord. This proposed AD would require repetitive inspections for any cracking of a certain fuselage frame inner chord; for certain airplanes, an identification of the material of a certain fuselage frame inner chord; and applicable corrective actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 3, 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 90740–5600; 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. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0340. 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– 0340; 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. VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 FOR FURTHER INFORMATION CONTACT: Muoi Vuong, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5205; fax: 562–627–5210; email: Muoi.Vuong@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0340; Directorate Identifier 2017– NM–002–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 We have received a report indicating that an operator found a 0.406-inch-long crack in the fuselage station (STA) 1380 frame inner chord, originating from a fastener hole between fuselage stringers S–25R and S–26R. The crack was found during frame web corrosion removal on an airplane with a 7075–T73 aluminum alloy at the fuselage STA 1380 frame inner chord. Boeing received five other reports of cracking on airplanes with a 7075–T73 aluminum alloy at the fuselage STA 1380 frame inner chord. Boeing has determined that existing internal zonal general visual and detailed structural inspections of the number 2 cargo door cutout are not adequate to reliably detect a crack before it grows to a critical length. This condition, if not corrected, could result in the door opening during flight, and result in rapid decompression of the airplane and the inability to sustain loads required for continued safe flight and landing. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. The service information PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 describes procedures for repetitive surface high frequency eddy current (HFEC) inspections for any cracking of the fuselage STA 1380 frame inner chord; an identification of the material (an inspection or measurement) of the fuselage STA 1380 frame inner chord; and applicable corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–20++– +++++. The phrase ‘‘corrective actions’’ is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 757– 53A0101, dated November 8, 2016, specifies to contact the manufacturer for certain instructions, but this proposed AD would require using repair methods, modification deviations, and alteration deviations in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 588 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\19MYP1.SGM 19MYP1 Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules 22917 ESTIMATED COSTS Action Labor cost Surface HFEC inspection ... 5 work-hours × $85 per hour = $425 per inspection cycle. Up to 2 work-hours × $85 per hour = $170. Identify the material ............ Parts cost Cost per product $0 $425 per inspection cycle ....... $249,900 per inspection cycle. 0 Up to $170 .............................. Up to $99,960. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. List of Subjects in 14 CFR Part 39 Authority for This Rulemaking The Proposed Amendment 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. sradovich on DSK3GMQ082PROD with PROPOSALS Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 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– 2017–0340; Directorate Identifier 2017– NM–002–AD. (a) Comments Due Date We must receive comments by July 3, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757–200, –200PF, and –300 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracking found at the fuselage station (STA) 1380 frame inner chord. We are issuing this AD to detect and correct such cracks, which could result in the door opening during flight, and result in rapid decompression of the airplane and the inability to sustain loads required for continued safe flight and landing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection for Group 1 Airplanes For Group 1 airplanes as identified in Boeing Alert Service Bulletin 757–53A0101, PO 00000 Cost on U.S. operators Frm 00014 Fmt 4702 Sfmt 4702 dated November 8, 2016: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016; except as specified in paragraph (i)(1) of this AD, do a surface high frequency eddy current (HFEC) inspection for any cracking of the fuselage STA 1380 frame inner chord, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016; except as specified in paragraph (i)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the surface HFEC inspection, thereafter, at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. (h) Inspection for Group 2 Airplanes For Group 2 airplanes as identified in Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016; except as specified in paragraph (i)(1) of this AD, identify the material of the fuselage STA 1380 frame inner chord, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. (1) If the fuselage STA 1380 frame inner chord material 2024–T42 aluminum alloy is found during any identification required by paragraph (h) of this AD: No further action is required by this AD for that airplane. (2) If the fuselage STA 1380 frame inner chord material 7075–T73 aluminum alloy is found during any identification required by paragraph (h) of this AD: Before further flight, do a surface HFEC inspection for any cracking of the fuselage STA 1380 frame inner chord, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016; except as specified in paragraph (i)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the surface HFEC inspection, thereafter, at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. (i) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. E:\FR\FM\19MYP1.SGM 19MYP1 22918 Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules 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. (j) 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 (k)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-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, 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) Except as required by paragraph (i)(2) of this AD: For service information that contains steps that are labeled as 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. sradovich on DSK3GMQ082PROD with PROPOSALS (2) Where Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, specifies to contact Boeing for appropriate action and identifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Issued in Renton, Washington, on May 10, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10033 Filed 5–18–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Examining the AD Docket 14 CFR Part 39 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0476; 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 Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. [Docket No. FAA–2017–0476; Directorate Identifier 2016–NM–110–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2014–08– 01, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014–08–01 currently requires an inspection for part numbers of the interconnecting struts and, for affected interconnecting struts, identification of the part and serial numbers of the associated target and proximity sensors and replacement or re-identification of the flap interconnecting strut if necessary. Since we issued AD 2014– 08–01, we have determined that certain airplanes must be inspected to verify the interconnecting strut part number. This proposed AD would add airplanes to the applicability. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR (k) Related Information 11.43 and 11.45, by any of the following (1) For more information about this AD, methods: contact Muoi Vuong, Aerospace Engineer, • Federal eRulemaking Portal: Go to Airframe Branch, ANM–120L, FAA, Los http://www.regulations.gov. Follow the Angeles ACO, 3960 Paramount Boulevard, instructions for submitting comments. Lakewood, CA 90712–4137; phone: 562–627– • Fax: 202–493–2251. 5205; fax: 562–627–5210; email: • Mail: U.S. Department of Muoi.Vuong@faa.gov. Transportation, Docket Operations, M– (2) For service information identified in 30, West Building Ground Floor, Room this AD, contact Boeing Commercial W12–140, 1200 New Jersey Avenue SE., Airplanes, Attention: Contractual & Data Washington, DC 20590. Services (C&DS), 2600 Westminster Blvd., VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 • 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 Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.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. SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–1405; fax 425–227–1149. 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–2017–0476; Directorate Identifier 2016–NM–110–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 based on 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. E:\FR\FM\19MYP1.SGM 19MYP1

Agencies

[Federal Register Volume 82, Number 96 (Friday, May 19, 2017)]
[Proposed Rules]
[Pages 22915-22918]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10033]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0340; Directorate Identifier 2017-NM-002-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 757-200, -200PF, and -300 series 
airplanes. This proposed AD was prompted by reports

[[Page 22916]]

of cracking found at a certain fuselage frame inner chord. This 
proposed AD would require repetitive inspections for any cracking of a 
certain fuselage frame inner chord; for certain airplanes, an 
identification of the material of a certain fuselage frame inner chord; 
and applicable corrective actions. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 3, 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 90740-5600; 
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. It is also 
available on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0340.

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-
0340; 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: Muoi Vuong, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5205; fax: 562-627-5210; email: Muoi.Vuong@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0340; 
Directorate Identifier 2017-NM-002-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

    We have received a report indicating that an operator found a 
0.406-inch-long crack in the fuselage station (STA) 1380 frame inner 
chord, originating from a fastener hole between fuselage stringers S-
25R and S-26R. The crack was found during frame web corrosion removal 
on an airplane with a 7075-T73 aluminum alloy at the fuselage STA 1380 
frame inner chord. Boeing received five other reports of cracking on 
airplanes with a 7075-T73 aluminum alloy at the fuselage STA 1380 frame 
inner chord. Boeing has determined that existing internal zonal general 
visual and detailed structural inspections of the number 2 cargo door 
cutout are not adequate to reliably detect a crack before it grows to a 
critical length. This condition, if not corrected, could result in the 
door opening during flight, and result in rapid decompression of the 
airplane and the inability to sustain loads required for continued safe 
flight and landing.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016. The service information describes procedures for 
repetitive surface high frequency eddy current (HFEC) inspections for 
any cracking of the fuselage STA 1380 frame inner chord; an 
identification of the material (an inspection or measurement) of the 
fuselage STA 1380 frame inner chord; and applicable corrective actions. 
This service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-20++-+++++.
    The phrase ``corrective actions'' is used in this proposed AD. 
Corrective actions correct or address any condition found. Corrective 
actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, 
specifies to contact the manufacturer for certain instructions, but 
this proposed AD would require using repair methods, modification 
deviations, and alteration deviations in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 588 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

[[Page 22917]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                   Labor cost       Parts cost               Cost per product                      Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Surface HFEC inspection............  5 work-hours x                $0  $425 per inspection cycle............  $249,900 per inspection cycle.
                                      $85 per hour =
                                      $425 per
                                      inspection
                                      cycle.
Identify the material..............  Up to 2 work-                  0  Up to $170...........................  Up to $99,960.
                                      hours x $85 per
                                      hour = $170.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

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 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-2017-0340; Directorate Identifier 
2017-NM-002-AD.

(a) Comments Due Date

    We must receive comments by July 3, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, -200PF, and 
-300 series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 757-53A0101, dated November 8, 
2016.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracking found at the 
fuselage station (STA) 1380 frame inner chord. We are issuing this 
AD to detect and correct such cracks, which could result in the door 
opening during flight, and result in rapid decompression of the 
airplane and the inability to sustain loads required for continued 
safe flight and landing.

(f) Compliance

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

(g) Inspection for Group 1 Airplanes

    For Group 1 airplanes as identified in Boeing Alert Service 
Bulletin 757-53A0101, dated November 8, 2016: At the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-53A0101, dated November 8, 2016; except as specified in 
paragraph (i)(1) of this AD, do a surface high frequency eddy 
current (HFEC) inspection for any cracking of the fuselage STA 1380 
frame inner chord, and do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-53A0101, dated November 8, 2016; except as 
specified in paragraph (i)(2) of this AD. Do all applicable 
corrective actions before further flight. Repeat the surface HFEC 
inspection, thereafter, at the times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016.

(h) Inspection for Group 2 Airplanes

    For Group 2 airplanes as identified in Boeing Alert Service 
Bulletin 757-53A0101, dated November 8, 2016: At the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-53A0101, dated November 8, 2016; except as specified in 
paragraph (i)(1) of this AD, identify the material of the fuselage 
STA 1380 frame inner chord, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016.
    (1) If the fuselage STA 1380 frame inner chord material 2024-T42 
aluminum alloy is found during any identification required by 
paragraph (h) of this AD: No further action is required by this AD 
for that airplane.
    (2) If the fuselage STA 1380 frame inner chord material 7075-T73 
aluminum alloy is found during any identification required by 
paragraph (h) of this AD: Before further flight, do a surface HFEC 
inspection for any cracking of the fuselage STA 1380 frame inner 
chord, and do all applicable corrective actions, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
757-53A0101, dated November 8, 2016; except as specified in 
paragraph (i)(2) of this AD. Do all applicable corrective actions 
before further flight. Repeat the surface HFEC inspection, 
thereafter, at the times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016.

(i) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.

[[Page 22918]]

    (2) Where Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016, specifies to contact Boeing for appropriate action 
and identifies that action as ``RC'' (Required for Compliance): 
Before further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (j) of this 
AD.

(j) 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 (k)(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) Except as required by paragraph (i)(2) of this AD: For 
service information that contains steps that are labeled as 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 Muoi Vuong, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5205; fax: 562-627-5210; email: Muoi.Vuong@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 10, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10033 Filed 5-18-17; 8:45 am]
 BILLING CODE 4910-13-P