Airworthiness Directives; The Boeing Company Airplanes, 44301-44304 [2017-19767]

Download as PDF Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations This unsafe condition, if not corrected, could result in failure of the HPC impeller, uncontained HPC impeller release, damage to the engine, and damage to the airplane/ helicopter. DEPARTMENT OF TRANSPORTATION (f) Compliance [Docket No. FAA–2016–9185; Product Identifier 2016–NM–077–AD; Amendment 39–19040; AD 2017–19–10] Comply with this AD within the compliance times specified, unless already done. (1) For CT7–9B engines, remove the affected HPC impeller from service at the next engine shop visit after the effective date of this AD, or prior to accumulating 12,000 cycles since new, whichever is earlier. (2) For CT7–8A engines, remove the affected HPC impeller from service at the next engine shop visit after the effective date of this AD, or prior to accumulating 1,500 engine hours after the effective date of this AD, whichever is earlier. (g) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (i) Related Information (1) For more information about this AD, contact Kasra Sharifi, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7773; fax: 781–238–7199; email: kasra.sharifi@faa.gov. (2) GE Service Bulletin CT7–TP S/B 72– 0524, dated June 16, 2016, can be obtained from GE using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact General Electric Company, GE–Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; fax: 513–552–3329; email: geae.aoc@ge.com. (4) You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. (j) Material Incorporated by Reference 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757–200, –200PF, and –200CB series airplanes. This AD was prompted by an analysis of the cam support assemblies of the main cargo door (MCD) that indicated that the existing maintenance program for the cam support assemblies is not adequate to reliably detect cracks before two adjacent cam support assemblies could fail. This AD requires an inspection to determine part numbers, repetitive inspections to detect cracking of affected cam support assemblies of the MCD, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 27, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 27, 2017. 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, 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–2016– 9185. SUMMARY: Examining the AD Docket None. Issued in Burlington, Massachusetts, on September 13, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–19961 Filed 9–21–17; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 Federal Aviation Administration 16:02 Sep 21, 2017 Jkt 241001 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9185; 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 44301 contains this final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, 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: Chandra Ramdoss, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5239; fax: 562–627– 5210; email: chandraduth.ramdoss@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 757–200, –200PF, and –200CB series airplanes. The NPRM published in the Federal Register on October 4, 2016 (81 FR 68371) (‘‘the NPRM’’). The NPRM was prompted by an analysis of the cam support assemblies of the MCD that indicated that the existing maintenance program for the cam support assemblies is not adequate to reliably detect cracks before two adjacent cam support assemblies could fail. The NPRM proposed to require an inspection to determine part numbers, repetitive inspections to detect cracking of affected cam support assemblies of the MCD, and replacement if necessary. We are issuing this AD to detect and correct cracking of the cam support assemblies of the MCD, which could result in reduced structural integrity of the MCD and consequent rapid decompression of the airplane. Comments We 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. Requests To Revise Applicability Boeing, Delta Air Lines (DAL), European Air Transport Leipzig GmbH (EAT), DHL Express (DHL), FedEx Express (FedEx), and United Airlines (UAL) requested that we revise the proposed AD applicability. DAL and UAL requested that airplanes that do not have a MCD be excluded from the AD applicability. Three of these commenters requested that the actions of the service information be applicable only to E:\FR\FM\22SER1.SGM 22SER1 44302 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations airplanes in the service information effectivity. These commenters explained that the service information effectivity includes only airplanes that have a MCD installed by Boeing, either as a Boeing factory-delivered freighter or as a Boeing Supplemental Type Certificate (STC)converted freighter, and not airplanes that have been converted to a freighter by a non-Boeing STC. EAT and DHL requested that we revise the applicability of the proposed AD to exclude Model 757 airplanes with passenger to freighter modification STC ST01529SE by Precision Conversions. FedEx requested that we either withdraw the NPRM and issue a new one, to include a separate section for airplanes modified under VT Mobile Aerospace Engineering STC ST03562AT, or exempt the airplanes modified by that STC from the NPRM and issue a new NPRM for airplanes modified by that STC. FedEx also requested that we revise the NPRM to mandate, for Model 757–200 airplanes modified in accordance with STC ST03562AT, VT Mobile Aerospace Engineering Service Bulletin MAE757SF–SB–52–l 601, Revision 0, dated April 15, 2016, or a subsequent revision, instead of Boeing Alert Service Bulletin 757–52A0094, dated December 23, 2015. FedEx explained that the MCD that is installed by the Precision Conversion STC is different than that installed by Boeing or VT Mobile Aerospace Engineering and does not have the affected cam support fittings installed. FedEx stated that it prefers the VT Mobile Aerospace Engineering service information for modifying airplanes instead of the Boeing service information, since Boeing does not provide support for the VT Mobile Aerospace STC, and any discrepancies or questions on the Boeing service information would be addressed by Boeing based on goodwill, rather than by contractual agreement. We partially agree with the commenters’ requests. We agree that the unsafe condition does not apply to Model 757–200 airplanes that do not have a MCD and to airplanes modified from passenger to freighter in accordance with Precision Conversions STC ST01529SE. The unsafe condition applies only to MCD cam support assemblies with the specified part numbers. We disagree that the AD should apply only to Boeing converted freighters. We also disagree that a separate AD should be issued to address Model 757–200 freighters modified by STC ST03562AT or any of the other passenger-to-freighter modification STCs because these support assemblies having affected part VerDate Sep<11>2014 16:02 Sep 21, 2017 Jkt 241001 numbers could be installed during original aircraft manufacture, or during passenger-to-freighter modification. The unsafe condition applies only to airplanes with certain part number cam support assemblies installed, and it does not apply to Model 757–200 airplanes that do not have a MCD. Paragraphs (g) and (h) of this AD list the part numbers of the cam support assemblies that have the unsafe condition. We have confirmed that the cam support assemblies having affected part numbers are not installed on Model 757 airplanes as part of the Precision Conversions STC ST01529SE passengerto-freighter conversion. We have revised the SUMMARY section, Discussion section, and paragraph (c) of this AD to state that the AD applies to all Model 757–200, –200PF, and –200CB series airplanes equipped with a MCD, except those airplanes that have been converted from a passenger to freighter configuration in accordance with STC ST01529SE. We expect that the actions specified in Boeing Alert Service Bulletin 757– 52A0094, Revision 2, dated May 2, 2017 (‘‘ASB 757–52A0094, R2’’), can be accomplished on airplanes that are not identified in that service information. In addition, we do not consider it appropriate to include various provisions in an AD applicable only to an operator’s unique configuration of affected airplanes. However, if an operator with a Model 757–200 freighter cannot accomplish the required actions specified in the service information, or prefers to use different service information that is specific to their design (such as FedEx’s request to use VT Mobile Aerospace Engineering Service Bulletin MAE757SF–SB–52–l 601, Revision 0, dated April 15, 2016), an alternative method of compliance (AMOC) can be requested in accordance with paragraph (j) of this AD. Requests To Revise the Compliance Time Boeing and FedEx requested that we revise the compliance time in paragraph (g)(l) of the proposed AD from ‘‘18,000 total flight cycles’’ to ‘‘18,000 door flight cycles.’’ The commenters explained that some of the affected airplanes have been converted from passenger to freighter airplanes, and for these converted airplanes, the cam support assemblies were installed at the time of the aircraft conversion, not when the airplanes were produced. The commenters stated that, for these converted airplanes, the initial compliance time for inspection should be based on the number of flight cycles since the part has been installed. In addition, Boeing stated that ASB 757– PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 52A0094, R2, was revised to change the inspection threshold for Boeing converted freighter airplanes to total flight cycles after freighter conversion redelivery. We agree with the commenters’ request. For airplanes that have been converted to freighters, the compliance time for the initial inspection should be based on the number of cycles the cam support assembly has been in service. We have revised paragraph (g)(1) of this AD accordingly. Request To Withdraw the NPRM and Reference Revised Service Information FedEx requested that we withdraw the NPRM and issue a new NPRM to require compliance with ASB 757– 52A0094, R2, instead of Boeing Alert Service Bulletin 757–52A0094, dated December 23, 2015. We partially agree with the commenter’s request. We agree with the commenter’s request to reference ASB 757–52A0094, R2, as the appropriate source of service information. Revision 1 of Boeing Alert Service Bulletin 757– 52A0094, dated April 21, 2016 (‘‘ASB 757–52A0094, R1’’), removed one airplane from the effectivity and updated some references and publications affected. ASB 757– 52A0094, R2, removed non-Boeing-STCconverted freighter airplanes from the effectivity and changed the initial compliance time for the converted freighter airplanes to flight cycles after freighter conversion redelivery. We disagree with withdrawing the NPRM and reissuing a new NPRM requiring compliance with ASB 757– 52A0094, R2, because doing so would unnecessarily delay issuance of the final rule. Additionally, the compliance time can be corrected in the final rule without the need for a supplemental NPRM since the corrected compliance time will provide additional time for the converted freighter airplanes and will not reduce the initial compliance time for any airplane. We have revised this AD to refer to ASB 757–52A0094, R2, as the appropriate source of service information. We have also added paragraph (i) to this AD to provide credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 757–52A0094, dated December 23, 2015; or ASB 757–52A0094, R1. We have redesignated subsequent paragraphs accordingly. Request To Correct Manual Reference in the Service Information United Parcel Service (UPS) requested that we revise paragraph (h) of the E:\FR\FM\22SER1.SGM 22SER1 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations proposed AD to specify use of Airplane Maintenance Manual (AMM) 52–32–11 in lieu of Component Maintenance Manual (CMM) 52–32–03 for the cam and bell-crank assembly installation. UPS explained that Boeing Alert Service Bulletin 757–52A0094, dated December 23, 2015, included an incorrect manual reference. We partially agree with the commenter’s request. We agree that the manual reference is incorrect in Boeing Alert Service Bulletin 757–52A0094, dated December 23, 2015. The incorrect reference was changed in ASB 757– 52A0094, R2, and, as explained previously, ASB 757–52A0094, R2, is referenced as the appropriate source of service information in this AD. No further change is necessary in this regard. Conclusion We 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. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. 44303 Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 757–52A0094, Revision 2, dated May 2, 2017. This service information describes procedures for an ultrasonic inspection of the cam support assemblies of the main cargo door, and replacement of the cam support assemblies. 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. Costs of Compliance We estimate that this AD will affect 212 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Parts cost Action Labor cost Inspection ........ 6 work-hours × $85 per hour = $510 per inspection cycle. We estimate the following costs to do any necessary replacements that would Cost per product $0 Cost on U.S. operators $510 per inspection cycle .......... be required based on the results of the inspection. We have no way of $108,120 per inspection cycle. determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement (per pair of cam support assemblies) .... 60 work-hours × $85 per hour = $5,100 ...................... 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, VerDate Sep<11>2014 16:02 Sep 21, 2017 Jkt 241001 Parts cost $15,298 Cost per product $20,398 as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. (2) Is not a ‘‘significant rule’’ under 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. Regulatory Findings List of Subjects in 14 CFR Part 39 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, Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 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 1. The authority citation for part 39 continues to read as follows: ■ E:\FR\FM\22SER1.SGM 22SER1 44304 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations 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): ■ 2017–19–10 The Boeing Company: Amendment 39–19040; Docket No. FAA–2016–9185; Product Identifier 2016–NM–077–AD. (a) Effective Date This AD is effective October 27, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757–200, –200PF, and –200CB series airplanes, certificated in any category, equipped with a main cargo door (MCD), except those airplanes that have been converted from a passenger to freighter configuration in accordance with Supplemental Type Certificate ST01529SE (http://rgl.faa.gov/Regulatory_and_ Guidance_Library/rgstc.nsf/0/9c0283b6 ce0b9ff18625806b007340b9/$FILE/ ST01529SE.pdf). (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Unsafe Condition This AD was prompted by an analysis of the cam support assemblies of the MCD that indicated that the existing maintenance program for the cam support assemblies is not adequate to reliably detect cracks before two adjacent cam support assemblies could fail. We are issuing this AD to detect and correct cracking of the cam support assemblies of the MCD, which could result in reduced structural integrity of the MCD and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine Part Numbers At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Inspect the cam support assemblies of the MCD to determine whether part number (P/ N) 69–23588–5, 69–23588–6, 69–23588–7, 69–23588–8, 69–23588–9, or 69–23588–10 is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number(s) of the cam support assemblies of the MCD can be conclusively determined from that review. (1) Before the accumulation of 18,000 total flight cycles since installation of the MCD. If the flight cycles since installation of the MCD are not known, use total airplane flight cycles. (2) Within 2,743 flight cycles or 27 months after the effective date of this AD, whichever occurs later. VerDate Sep<11>2014 16:02 Sep 21, 2017 Jkt 241001 (h) Inspections and Corrective Actions If, during the inspection required by paragraph (g) of this AD, any cam support assembly of the MCD having P/N 69–23588– 5, 69–23588–6, 69–23588–7, 69–23588–8, 69–23588–9, or 69–23588–10 is determined to be installed: At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD, do an ultrasonic inspection to detect cracking of the affected cam support assemblies of the MCD; and do all applicable replacements; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–52A0094, Revision 2, dated May 2, 2017. Do all applicable replacements before further flight. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles. Replacement of a cam support assembly of the MCD does not terminate the repetitive inspections required by this paragraph. (i) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 757–52A0094, dated December 23, 2015; or Boeing Alert Service Bulletin 757– 52A0094, Revision 1, dated April 21, 2016. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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)(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 Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (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. PO 00000 Frm 00006 Fmt 4700 Sfmt 9990 (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 Chandra Ramdoss, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (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 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 Alert Service Bulletin 757– 52A0094, Revision 2, dated May 2, 2017. (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, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 7, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–19767 Filed 9–21–17; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\22SER1.SGM 22SER1

Agencies

[Federal Register Volume 82, Number 183 (Friday, September 22, 2017)]
[Rules and Regulations]
[Pages 44301-44304]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19767]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9185; Product Identifier 2016-NM-077-AD; Amendment 
39-19040; AD 2017-19-10]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 757-200, -200PF, and -200CB series airplanes. 
This AD was prompted by an analysis of the cam support assemblies of 
the main cargo door (MCD) that indicated that the existing maintenance 
program for the cam support assemblies is not adequate to reliably 
detect cracks before two adjacent cam support assemblies could fail. 
This AD requires an inspection to determine part numbers, repetitive 
inspections to detect cracking of affected cam support assemblies of 
the MCD, and replacement if necessary. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective October 27, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 27, 
2017.

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, 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-2016-
9185.

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-2016-
9185; 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 final rule, the regulatory evaluation, any comments 
received, and other information. The address for the Docket Office 
(phone: 800-647-5527) is Docket Management Facility, 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: Chandra Ramdoss, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-
5210; email: chandraduth.ramdoss@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all The Boeing Company 
Model 757-200, -200PF, and -200CB series airplanes. The NPRM published 
in the Federal Register on October 4, 2016 (81 FR 68371) (``the 
NPRM''). The NPRM was prompted by an analysis of the cam support 
assemblies of the MCD that indicated that the existing maintenance 
program for the cam support assemblies is not adequate to reliably 
detect cracks before two adjacent cam support assemblies could fail. 
The NPRM proposed to require an inspection to determine part numbers, 
repetitive inspections to detect cracking of affected cam support 
assemblies of the MCD, and replacement if necessary. We are issuing 
this AD to detect and correct cracking of the cam support assemblies of 
the MCD, which could result in reduced structural integrity of the MCD 
and consequent rapid decompression of the airplane.

Comments

    We 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.

Requests To Revise Applicability

    Boeing, Delta Air Lines (DAL), European Air Transport Leipzig GmbH 
(EAT), DHL Express (DHL), FedEx Express (FedEx), and United Airlines 
(UAL) requested that we revise the proposed AD applicability. DAL and 
UAL requested that airplanes that do not have a MCD be excluded from 
the AD applicability.
    Three of these commenters requested that the actions of the service 
information be applicable only to

[[Page 44302]]

airplanes in the service information effectivity. These commenters 
explained that the service information effectivity includes only 
airplanes that have a MCD installed by Boeing, either as a Boeing 
factory-delivered freighter or as a Boeing Supplemental Type 
Certificate (STC)-converted freighter, and not airplanes that have been 
converted to a freighter by a non-Boeing STC.
    EAT and DHL requested that we revise the applicability of the 
proposed AD to exclude Model 757 airplanes with passenger to freighter 
modification STC ST01529SE by Precision Conversions.
    FedEx requested that we either withdraw the NPRM and issue a new 
one, to include a separate section for airplanes modified under VT 
Mobile Aerospace Engineering STC ST03562AT, or exempt the airplanes 
modified by that STC from the NPRM and issue a new NPRM for airplanes 
modified by that STC. FedEx also requested that we revise the NPRM to 
mandate, for Model 757-200 airplanes modified in accordance with STC 
ST03562AT, VT Mobile Aerospace Engineering Service Bulletin MAE757SF-
SB-52-l 601, Revision 0, dated April 15, 2016, or a subsequent 
revision, instead of Boeing Alert Service Bulletin 757-52A0094, dated 
December 23, 2015. FedEx explained that the MCD that is installed by 
the Precision Conversion STC is different than that installed by Boeing 
or VT Mobile Aerospace Engineering and does not have the affected cam 
support fittings installed. FedEx stated that it prefers the VT Mobile 
Aerospace Engineering service information for modifying airplanes 
instead of the Boeing service information, since Boeing does not 
provide support for the VT Mobile Aerospace STC, and any discrepancies 
or questions on the Boeing service information would be addressed by 
Boeing based on goodwill, rather than by contractual agreement.
    We partially agree with the commenters' requests. We agree that the 
unsafe condition does not apply to Model 757-200 airplanes that do not 
have a MCD and to airplanes modified from passenger to freighter in 
accordance with Precision Conversions STC ST01529SE. The unsafe 
condition applies only to MCD cam support assemblies with the specified 
part numbers.
    We disagree that the AD should apply only to Boeing converted 
freighters. We also disagree that a separate AD should be issued to 
address Model 757-200 freighters modified by STC ST03562AT or any of 
the other passenger-to-freighter modification STCs because these 
support assemblies having affected part numbers could be installed 
during original aircraft manufacture, or during passenger-to-freighter 
modification. The unsafe condition applies only to airplanes with 
certain part number cam support assemblies installed, and it does not 
apply to Model 757-200 airplanes that do not have a MCD.
    Paragraphs (g) and (h) of this AD list the part numbers of the cam 
support assemblies that have the unsafe condition. We have confirmed 
that the cam support assemblies having affected part numbers are not 
installed on Model 757 airplanes as part of the Precision Conversions 
STC ST01529SE passenger-to-freighter conversion. We have revised the 
SUMMARY section, Discussion section, and paragraph (c) of this AD to 
state that the AD applies to all Model 757-200, -200PF, and -200CB 
series airplanes equipped with a MCD, except those airplanes that have 
been converted from a passenger to freighter configuration in 
accordance with STC ST01529SE.
    We expect that the actions specified in Boeing Alert Service 
Bulletin 757-52A0094, Revision 2, dated May 2, 2017 (``ASB 757-52A0094, 
R2''), can be accomplished on airplanes that are not identified in that 
service information. In addition, we do not consider it appropriate to 
include various provisions in an AD applicable only to an operator's 
unique configuration of affected airplanes. However, if an operator 
with a Model 757-200 freighter cannot accomplish the required actions 
specified in the service information, or prefers to use different 
service information that is specific to their design (such as FedEx's 
request to use VT Mobile Aerospace Engineering Service Bulletin 
MAE757SF-SB-52-l 601, Revision 0, dated April 15, 2016), an alternative 
method of compliance (AMOC) can be requested in accordance with 
paragraph (j) of this AD.

Requests To Revise the Compliance Time

    Boeing and FedEx requested that we revise the compliance time in 
paragraph (g)(l) of the proposed AD from ``18,000 total flight cycles'' 
to ``18,000 door flight cycles.'' The commenters explained that some of 
the affected airplanes have been converted from passenger to freighter 
airplanes, and for these converted airplanes, the cam support 
assemblies were installed at the time of the aircraft conversion, not 
when the airplanes were produced. The commenters stated that, for these 
converted airplanes, the initial compliance time for inspection should 
be based on the number of flight cycles since the part has been 
installed. In addition, Boeing stated that ASB 757-52A0094, R2, was 
revised to change the inspection threshold for Boeing converted 
freighter airplanes to total flight cycles after freighter conversion 
redelivery.
    We agree with the commenters' request. For airplanes that have been 
converted to freighters, the compliance time for the initial inspection 
should be based on the number of cycles the cam support assembly has 
been in service. We have revised paragraph (g)(1) of this AD 
accordingly.

Request To Withdraw the NPRM and Reference Revised Service Information

    FedEx requested that we withdraw the NPRM and issue a new NPRM to 
require compliance with ASB 757-52A0094, R2, instead of Boeing Alert 
Service Bulletin 757-52A0094, dated December 23, 2015.
    We partially agree with the commenter's request. We agree with the 
commenter's request to reference ASB 757-52A0094, R2, as the 
appropriate source of service information. Revision 1 of Boeing Alert 
Service Bulletin 757-52A0094, dated April 21, 2016 (``ASB 757-52A0094, 
R1''), removed one airplane from the effectivity and updated some 
references and publications affected. ASB 757-52A0094, R2, removed non-
Boeing-STC-converted freighter airplanes from the effectivity and 
changed the initial compliance time for the converted freighter 
airplanes to flight cycles after freighter conversion redelivery.
    We disagree with withdrawing the NPRM and reissuing a new NPRM 
requiring compliance with ASB 757-52A0094, R2, because doing so would 
unnecessarily delay issuance of the final rule. Additionally, the 
compliance time can be corrected in the final rule without the need for 
a supplemental NPRM since the corrected compliance time will provide 
additional time for the converted freighter airplanes and will not 
reduce the initial compliance time for any airplane. We have revised 
this AD to refer to ASB 757-52A0094, R2, as the appropriate source of 
service information. We have also added paragraph (i) to this AD to 
provide credit for actions required by paragraph (h) of this AD, if 
those actions were performed before the effective date of this AD using 
Boeing Alert Service Bulletin 757-52A0094, dated December 23, 2015; or 
ASB 757-52A0094, R1. We have redesignated subsequent paragraphs 
accordingly.

Request To Correct Manual Reference in the Service Information

    United Parcel Service (UPS) requested that we revise paragraph (h) 
of the

[[Page 44303]]

proposed AD to specify use of Airplane Maintenance Manual (AMM) 52-32-
11 in lieu of Component Maintenance Manual (CMM) 52-32-03 for the cam 
and bell-crank assembly installation. UPS explained that Boeing Alert 
Service Bulletin 757-52A0094, dated December 23, 2015, included an 
incorrect manual reference.
    We partially agree with the commenter's request. We agree that the 
manual reference is incorrect in Boeing Alert Service Bulletin 757-
52A0094, dated December 23, 2015. The incorrect reference was changed 
in ASB 757-52A0094, R2, and, as explained previously, ASB 757-52A0094, 
R2, is referenced as the appropriate source of service information in 
this AD. No further change is necessary in this regard.

Conclusion

    We 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. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We 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

    We reviewed Boeing Alert Service Bulletin 757-52A0094, Revision 2, 
dated May 2, 2017. This service information describes procedures for an 
ultrasonic inspection of the cam support assemblies of the main cargo 
door, and replacement of the cam support assemblies. 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.

Costs of Compliance

    We estimate that this AD will affect 212 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
         Action                Labor cost         Parts cost                  Cost per product                          Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection..............  6 work-hours x $85                $0  $510 per inspection cycle..................  $108,120 per inspection cycle.
                           per hour = $510 per
                           inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement (per pair of cam support            60 work-hours x $85 per hour =           $15,298         $20,398
 assemblies).                                    $5,100.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

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) Is not a ``significant rule'' under 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.

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:


[[Page 44304]]


    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):

2017-19-10 The Boeing Company: Amendment 39-19040; Docket No. FAA-
2016-9185; Product Identifier 2016-NM-077-AD.

(a) Effective Date

    This AD is effective October 27, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, -200PF, and 
-200CB series airplanes, certificated in any category, equipped with 
a main cargo door (MCD), except those airplanes that have been 
converted from a passenger to freighter configuration in accordance 
with Supplemental Type Certificate ST01529SE (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
9c0283b6ce0b9ff18625806b007340b9/$FILE/ST01529SE.pdf).

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Unsafe Condition

    This AD was prompted by an analysis of the cam support 
assemblies of the MCD that indicated that the existing maintenance 
program for the cam support assemblies is not adequate to reliably 
detect cracks before two adjacent cam support assemblies could fail. 
We are issuing this AD to detect and correct cracking of the cam 
support assemblies of the MCD, which could result in reduced 
structural integrity of the MCD and consequent rapid decompression 
of the airplane.

(f) Compliance

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

(g) Inspection To Determine Part Numbers

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Inspect the cam support assemblies of the MCD to 
determine whether part number (P/N) 69-23588-5, 69-23588-6, 69-
23588-7, 69-23588-8, 69-23588-9, or 69-23588-10 is installed. A 
review of airplane maintenance records is acceptable in lieu of this 
inspection if the part number(s) of the cam support assemblies of 
the MCD can be conclusively determined from that review.
    (1) Before the accumulation of 18,000 total flight cycles since 
installation of the MCD. If the flight cycles since installation of 
the MCD are not known, use total airplane flight cycles.
    (2) Within 2,743 flight cycles or 27 months after the effective 
date of this AD, whichever occurs later.

(h) Inspections and Corrective Actions

    If, during the inspection required by paragraph (g) of this AD, 
any cam support assembly of the MCD having P/N 69-23588-5, 69-23588-
6, 69-23588-7, 69-23588-8, 69-23588-9, or 69-23588-10 is determined 
to be installed: At the later of the times specified in paragraphs 
(g)(1) and (g)(2) of this AD, do an ultrasonic inspection to detect 
cracking of the affected cam support assemblies of the MCD; and do 
all applicable replacements; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-52A0094, Revision 
2, dated May 2, 2017. Do all applicable replacements before further 
flight. Repeat the inspection thereafter at intervals not to exceed 
6,000 flight cycles. Replacement of a cam support assembly of the 
MCD does not terminate the repetitive inspections required by this 
paragraph.

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(h) of this AD, if those actions were performed before the effective 
date of this AD using Boeing Alert Service Bulletin 757-52A0094, 
dated December 23, 2015; or Boeing Alert Service Bulletin 757-
52A0094, Revision 1, dated April 21, 2016.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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)(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 Branch, to make those findings. To be 
approved, the repair method, modification deviation, or alteration 
deviation must meet the certification basis of the airplane, and the 
approval must specifically refer to this AD.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(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 Chandra Ramdoss, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(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 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 Alert Service Bulletin 757-52A0094, Revision 2, dated 
May 2, 2017.
    (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, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 7, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-19767 Filed 9-21-17; 8:45 am]
 BILLING CODE 4910-13-P