Proposed Rules. Notice of proposed rulemaking (NPRM)

Agency: Federal Aviation Administration (FAA), DOT
Action: Notice of proposed rulemaking (NPRM)
Citation: FR Doc. 2016-23939 · RIN 2120-AA64 · Docket No. FAA-2016-9183; Directorate Identifier 2016-NM-059-AD · 14 CFR 39

Summary

We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes. This proposed AD was prompted by analysis of the cam support assemblies of the main cargo door that indicated the repetitive high frequency eddy current (HFEC) inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the main cargo door could fail. This proposed AD would require repetitive ultrasonic inspections for cracking of the cam support assemblies of the main cargo door and replacement if necessary. We are proposing this AD to detect and correct cracking of the cam support assemblies of the main cargo door. Such cracking could result in reduced structural integrity of the main cargo door and consequent rapid decompression of the airplane.

Dates

We must receive comments on this proposed AD by November 18, 2016.

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-2016-9183; Directorate Identifier 2016-NM-059-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 the analysis of the cam support assemblies of the main cargo door, part numbers 69-23588-5 and 69-23588-6, indicated that the repetitive HFEC inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the main cargo door could fail. This condition, if not corrected, could result in reduced structural integrity of the main cargo door and consequent rapid decompression of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. The service information describes procedures for an ultrasonic inspection of the cam support assemblies of the main cargo door for cracking, and replacement if necessary. 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-2016-9183. Differences Between This Proposed AD and the Service Information Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, only affects Model 707-300B and -300C airplanes. The applicability of this proposed AD extends to all Model 707 airplanes. Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, only affects certain part numbers. We are extending the list of affected part numbers to include 69-23588-1 and 69-23588-2, which are not referenced in Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. These differences exist to ensure all affected parts are inspected in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. For all airplanes affected by this AD, including airplanes not listed in the effectivity of Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, compliance with paragraph (h) of this AD must be done using Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. Therefore, an alternative method of compliance (AMOC) approval is not necessary for those airplanes if Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, is used. This difference has been coordinated with Boeing. Costs of Compliance We estimate that this proposed AD affects 12 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection 6 work-hours × $85 per hour = $510 per inspection cycle $0 $510 per inspection cycle $22,950 per inspection cycle. We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need this replacement: On-Condition Costs Action Labor cost Parts cost Cost per product Replacement 60 work-hours × $85 per hour = $5,100 $14,107 $19,207. 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 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-2016-9183; Directorate Identifier 2016-NM-059-AD. (a) Comments Due Date We must receive comments by November 18, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 707-100 Long Body, -200, -100B Long Body, and -100B Short Body series airplanes; and Model 707-300, -300B, -300C, and -400 series airplanes; certificated in any category, (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Unsafe Condition This AD was prompted by analysis of the cam support assemblies of the main cargo door that indicated the repetitive high frequency eddy current (HFEC) inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the main cargo door could fail. We are issuing this AD to detect and correct cracking of the cam support assemblies of the main cargo door. Such cracking could result in reduced structural integrity of the main cargo door 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 main cargo door to determine whether part number (P/N) 69-23588-1, 69-23588-2, 69-23588-5, 69-23588-6, 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 main cargo door can be conclusively determined from that review. (1) Before the accumulation of 18,000 total flight cycles. (2) Within 1,790 flight cycles or 24 months after the effective date of this AD, whichever occurs later. (h) Repetitive Inspections for the Cam Support Assemblies of the Main Cargo Door and Corrective Actions If, during any inspection required by paragraph (g) of this AD, any cam support assembly of the main cargo door having P/N 69-23588-1, 69-23588-2, 69-23588-5, 69-23588-6, 69-23588-9, or 69-23588-10 is determined to be installed: Except as required by paragraph (i) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, do an ultrasonic inspection to detect cracking of the affected cam support assemblies of the main cargo door, and do all applicable replacements, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. Do all applicable replacements before further flight. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. (i) Service Information Exception Where Boeing 707 Alert Service Bulletin A3542, dated February 12, 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. (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) 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 Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, extension 1; fax: 206-766-5680; 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 September 27, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-23939 Filed 10-3-16; 8:45 am]