Airworthiness Directives; The Boeing Company Airplanes, 68373-68376 [2016-23938]

Download as PDF Federal Register / Vol. 81, No. 192 / Tuesday, October 4, 2016 / Proposed Rules (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 main cargo door which 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 main cargo door, which 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) 69–23588–5, 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 main cargo door can be conclusively determined from that review. (1) Before the accumulation of 18,000 total flight cycles. (2) Within 2,743 flight cycles or 27 months after the effective date of this AD, whichever occurs later. mstockstill on DSK3G9T082PROD with PROPOSALS (h) Inspections 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 69–23588–5, 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 main cargo door; and do all applicable replacements; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–52A0094, dated December 23, 2015. Do all applicable replacements before further flight. Repeat the inspections thereafter at intervals not to exceed 6,000 flight cycles. Replacement of a cam support assembly of the main cargo door does not terminate the repetitive inspections required by this paragraph. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the VerDate Sep<11>2014 18:18 Oct 03, 2016 Jkt 241001 attention of the person identified in paragraph (j)(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) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or sub-step is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or sub-step. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, contact 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. 2016–23936 Filed 10–3–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 68373 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–9184; Directorate Identifier 2016–NM–060–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 all The Boeing Company Model 727 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. SUMMARY: 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: 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 ADDRESSES: E:\FR\FM\04OCP1.SGM 04OCP1 68374 Federal Register / Vol. 81, No. 192 / Tuesday, October 4, 2016 / Proposed Rules 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–2016– 9184. 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– 9184; 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: Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@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– 2016–9184; Directorate Identifier 2016– NM–060–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, having 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 Alert Service Bulletin 727–52A0151, 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– 9184. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 727– 52A0151, dated February 12, 2016, only affects Model 727C, 727–100C, and 727– 200F series airplanes. The applicability of this proposed AD extends to all Model 727 airplanes. Boeing Alert Service Bulletin 727–52A0151, 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 were not referenced in Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016. These differences exist to ensure all affected parts are inspected in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016. For all airplanes affected by this AD, including airplanes not listed in the effectivity of Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016, compliance with paragraph (h) of this AD must be done using Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016. Therefore, an alternative method of compliance (AMOC) approval is not necessary for those airplanes if Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016, is used. This difference has been coordinated with Boeing. Costs of Compliance We estimate that this proposed AD affects 45 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators Inspection ............................... mstockstill on DSK3G9T082PROD with PROPOSALS Action 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 VerDate Sep<11>2014 18:18 Oct 03, 2016 Jkt 241001 be required based on the results of the proposed inspection. We have no way of PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 determining the number of aircraft that might need this replacement: E:\FR\FM\04OCP1.SGM 04OCP1 Federal Register / Vol. 81, No. 192 / Tuesday, October 4, 2016 / Proposed Rules 68375 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 mstockstill on DSK3G9T082PROD with PROPOSALS 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, VerDate Sep<11>2014 18:18 Oct 03, 2016 Jkt 241001 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– 2016–9184; Directorate Identifier 2016–NM– 060–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 727, 727C, 727–100, 727– 100C, 727–200, and 727–200F 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) inspection 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 door can be conclusively determined from that review. (1) Before the accumulation of 18,000 total flight cycles. (2) Within 1,771 flight cycles or 27 months after the effective date of this AD, whichever occurs later. (h) Repetitive Inspections of 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: 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 main cargo door; and do all applicable replacements; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–52A0151, 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 Alert Service Bulletin 727–52A0151, dated February 12, 2016. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply. E:\FR\FM\04OCP1.SGM 04OCP1 68376 Federal Register / Vol. 81, No. 192 / Tuesday, October 4, 2016 / Proposed Rules (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, contact 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. 2016–23938 Filed 10–3–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9183; Directorate Identifier 2016–NM–059–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). mstockstill on DSK3G9T082PROD with PROPOSALS AGENCY: 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 SUMMARY: VerDate Sep<11>2014 18:18 Oct 03, 2016 Jkt 241001 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. 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: 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. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9183. ADDRESSES: 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– 9183; 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 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@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– 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. E:\FR\FM\04OCP1.SGM 04OCP1

Agencies

[Federal Register Volume 81, Number 192 (Tuesday, October 4, 2016)]
[Proposed Rules]
[Pages 68373-68376]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-23938]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-9184; Directorate Identifier 2016-NM-060-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 all 
The Boeing Company Model 727 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.

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: 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

[[Page 68374]]

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-2016-9184.

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-
9184; 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: Chandra Ramdoss, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@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-2016-9184; 
Directorate Identifier 2016-NM-060-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, having 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 Alert Service Bulletin 727-52A0151, 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-2016-9184.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016, 
only affects Model 727C, 727-100C, and 727-200F series airplanes. The 
applicability of this proposed AD extends to all Model 727 airplanes. 
Boeing Alert Service Bulletin 727-52A0151, 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 were 
not referenced in Boeing Alert Service Bulletin 727-52A0151, dated 
February 12, 2016. These differences exist to ensure all affected parts 
are inspected in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016. For 
all airplanes affected by this AD, including airplanes not listed in 
the effectivity of Boeing Alert Service Bulletin 727-52A0151, dated 
February 12, 2016, compliance with paragraph (h) of this AD must be 
done using Boeing Alert Service Bulletin 727-52A0151, dated February 
12, 2016. Therefore, an alternative method of compliance (AMOC) 
approval is not necessary for those airplanes if Boeing Alert Service 
Bulletin 727-52A0151, dated February 12, 2016, is used. This difference 
has been coordinated with Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 45 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  6 work-hours x $85               $0   $510 per inspection  $22,950 per
                                   per hour = $510                       cycle.               inspection cycle.
                                   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:

[[Page 68375]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement..................................  60 work-hours x $85 per hour =          $14,107          $19,207
                                                $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.

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-2016-9184; Directorate 
Identifier 2016-NM-060-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 727, 727C, 727-
100, 727-100C, 727-200, and 727-200F 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) inspection 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 1,771 flight cycles or 27 months after the effective 
date of this AD, whichever occurs later.

(h) Repetitive Inspections of 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: 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 
main cargo door; and do all applicable replacements; in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 727-52A0151, 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 Alert Service Bulletin 727-52A0151, dated 
February 12, 2016.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (j)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Los Angeles ACO, to make those findings. To be approved, 
the repair method, modification deviation, or alteration deviation 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(i)(4)(i) and (i)(4)(ii) of this AD apply.

[[Page 68376]]

    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(j) Related Information

    (1) For more information about this AD, contact 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. 2016-23938 Filed 10-3-16; 8:45 am]
 BILLING CODE 4910-13-P