Airworthiness Directives; The Boeing Company Airplanes, 43171-43173 [2017-19441]

Download as PDF Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9184; Product Identifier 2016–NM–060–AD; Amendment 39–19032; AD 2017–19–02] 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 727 airplanes. This AD was prompted by analysis of the cam support assemblies of the main cargo door (MCD) 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 MCD could fail. This AD requires repetitive ultrasonic inspections for cracking of the 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 19, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 19, 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– 9184. SUMMARY: rmajette on DSKBCKNHB2PROD with RULES 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 VerDate Sep<11>2014 15:11 Sep 13, 2017 Jkt 241001 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 727 airplanes. The NPRM published in the Federal Register on October 4, 2016 (81 FR 68373) (‘‘the NPRM’’). The NPRM was prompted by analysis of the cam support assemblies of the MCD that indicated the repetitive HFEC inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the MCD could fail. The NPRM proposed to require repetitive ultrasonic inspections for cracking of the 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. Such cracking 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 AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Revise Applicability Boeing stated that Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016, affects only Boeing factory and Boeing converted freighters, but the proposed AD extends the applicability to all Model 727 airplanes, including the ones that have been converted by non-Boeing STCs. We infer that the commenter is requesting that the actions of the service information only be required for Model 727 airplanes identified in the Effectivity paragraph of Boeing Alert PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 43171 Service Bulletin 727–52A0151, dated February 12, 2016. We agree that the applicability of the NPRM includes some airplanes that do not have the identified unsafe condition. The unsafe condition does not apply to Model 727 airplanes that do not have a MCD. Therefore, we have revised this AD to apply to Model 727 series airplanes equipped with a MCD. We disagree that the AD applicability should be limited to airplanes identified in the Effectivity paragraph of Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016, which only identifies Boeing factory and Boeingconverted freighters. Cam support assemblies having an affected part number, as specified in paragraphs (g) and (h) of this AD, could be installed during original aircraft manufacture, or during passenger to freighter modification. We expect that the actions specified in Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016, can be accomplished on airplanes that are not identified in that service information. However, if an operator cannot accomplish the required actions in the service information due to the airplane configuration, or prefers to use different service information that is specific to their design, they can request an alternative method of compliance (AMOC) in accordance with paragraph (j) of this AD. Request To Supersede AD 80–08–10 R1, Amendment 39–3830 (45 FR 46343, July 10, 1980) (‘‘AD 80–08–10 R1’’) Boeing requested that we revise the NPRM to supersede AD 80–08–10 R1. Boeing stated that AD 80–08–10 R1 mandates MCD cam support assemblies having part numbers (P/Ns) 69–23588– 1 and 69–23588–2 as specified in Boeing Service Bulletin 727–52A124. Boeing explained that the NPRM is adding cam support assemblies having P/Ns 69–23588–1 and 69–23588–2 to the list in Boeing Alert Service Bulletin 727–52A0151, dated February 12, 2016. Boeing asserted that the addition of these components to the list of affected parts would mean that the operators have to perform high frequency eddy current inspection of cam support assemblies having P/Ns 69–23588–1 and 69–23588–2 as specified in AD 80–08– 10 R1 and perform ultrasonic inspection of the same components as specified in the NPRM. Boeing explained that cracking initiates at the bottom of the lubrication hole inside the cam support fitting lug and the cracking is not visible until it breaks to the surface of the lug. Therefore, the subsurface detection capability of the ultrasonic inspection provides a more reliable inspection. E:\FR\FM\14SER1.SGM 14SER1 43172 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations We partially agree with Boeing’s request to supersede the inspections which are required by AD 80–08–10 R1. These inspections will overlap with the newly mandated repetitive inspections. We disagree with the request to revise this AD to supersede AD 80–08–10 R1. Instead, we have added paragraph (i) to this AD to state that completion of the initial inspection and all applicable replacements required by paragraph (h) of this AD terminates all requirements of AD 80–08–10 R1, for that airplane only. We have redesignated subsequent paragraphs accordingly. Request To Revise Compliance Time Boeing requested that we revise paragraph (g)(1) of the proposed AD from ‘‘before the accumulation of 18,000 total flight cycles’’ to ‘‘before the accumulation of 18,000 door flight cycles. If the door flight cycles are not known, use total airplane flight cycles.’’ Boeing explained that this change would provide relief for operators that have converted freighters by delaying the required inspection for the MCDs that have been in service less than 18,000 total door flight cycles, but are installed on the airplanes that have more than 18,000 total airframe flight cycles. We agree with Boeing’s request. For the airplanes that have been converted to freighters, the compliance time for the initial inspection should be based on the number of cycles that the cam support assembly has been in service. We have revised paragraph (g)(1) of this AD accordingly. 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 727–52A0151, dated February 12, 2016. This service information describes procedures for an ultrasonic inspection of the cam support assemblies of the MCD 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. Costs of Compliance We estimate that this AD will affect 45 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS 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 Parts cost 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 $22,950 per inspection cycle. determining the number of aircraft that might need this replacement: ON-CONDITION COSTS Labor cost Replacement ................................................................. rmajette on DSKBCKNHB2PROD with RULES Action 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 VerDate Sep<11>2014 15:11 Sep 13, 2017 Jkt 241001 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 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Parts cost $14,107 Cost per product $19,207 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. E:\FR\FM\14SER1.SGM 14SER1 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 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 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): ■ 2017–19–02 The Boeing Company: Amendment 39–19032; Docket No. FAA–2016–9184; Product Identifier 2016–NM–060–AD. (a) Effective Date This AD is effective October 19, 2017. (b) Affected ADs This AD affects AD 80–08–10 R1, Amendment 39–3830 (45 FR 46343, July 10, 1980). (c) Applicability This AD applies to The Boeing Company Model 727, 727C, 727–100, 727–100C, 727– 200, and 727–200F series airplanes, certificated in any category, equipped with a main cargo door (MCD). (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 MCD 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 MCD could fail. We are issuing this AD to detect and correct cracking of the cam support assemblies of the MCD. Such cracking could result in reduced structural integrity of the MCD and consequent rapid decompression of the airplane. rmajette on DSKBCKNHB2PROD with RULES (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) 69–23588–1, 69–23588–2, 69–23588–5, 69–23588–6, 69–23588–9, or 69–23588–10 is installed. A review of airplane maintenance VerDate Sep<11>2014 15:11 Sep 13, 2017 Jkt 241001 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 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 MCD 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 MCD; 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) Terminating Action for AD 80–08–10 R1, Amendment 39–3830 (45 FR 46343, July 10, 1980) Accomplishment of the initial inspection and all applicable replacements required by paragraph (h) of this AD terminates all requirements of AD 80–08–10 R1, Amendment 39–3830 (45 FR 46343, July 10, 1980), for that airplane only. (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) of this AD. Information may be emailed to: 9-ANMLAACO-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. PO 00000 Frm 00019 Fmt 4700 Sfmt 9990 43173 (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 For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5239; fax: 562–627–5210; email: chandraduth.ramdoss@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this 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 727– 52A0151, dated February 12, 2016. (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 August 31, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–19441 Filed 9–13–17; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\14SER1.SGM 14SER1

Agencies

[Federal Register Volume 82, Number 177 (Thursday, September 14, 2017)]
[Rules and Regulations]
[Pages 43171-43173]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19441]



[[Page 43171]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9184; Product Identifier 2016-NM-060-AD; Amendment 
39-19032; AD 2017-19-02]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 727 airplanes. This AD was prompted by 
analysis of the cam support assemblies of the main cargo door (MCD) 
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 MCD could fail. This AD requires repetitive ultrasonic inspections 
for cracking of the 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 19, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 19, 
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-
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 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 727 airplanes. The NPRM published in the Federal Register on 
October 4, 2016 (81 FR 68373) (``the NPRM''). The NPRM was prompted by 
analysis of the cam support assemblies of the MCD that indicated the 
repetitive HFEC inspections required by the existing maintenance 
program are not adequate to detect cracks before two adjacent cam 
support assemblies of the MCD could fail. The NPRM proposed to require 
repetitive ultrasonic inspections for cracking of the 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. Such cracking 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 AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Revise Applicability

    Boeing stated that Boeing Alert Service Bulletin 727-52A0151, dated 
February 12, 2016, affects only Boeing factory and Boeing converted 
freighters, but the proposed AD extends the applicability to all Model 
727 airplanes, including the ones that have been converted by non-
Boeing STCs.
    We infer that the commenter is requesting that the actions of the 
service information only be required for Model 727 airplanes identified 
in the Effectivity paragraph of Boeing Alert Service Bulletin 727-
52A0151, dated February 12, 2016. We agree that the applicability of 
the NPRM includes some airplanes that do not have the identified unsafe 
condition. The unsafe condition does not apply to Model 727 airplanes 
that do not have a MCD. Therefore, we have revised this AD to apply to 
Model 727 series airplanes equipped with a MCD.
    We disagree that the AD applicability should be limited to 
airplanes identified in the Effectivity paragraph of Boeing Alert 
Service Bulletin 727-52A0151, dated February 12, 2016, which only 
identifies Boeing factory and Boeing-converted freighters. Cam support 
assemblies having an affected part number, as specified in paragraphs 
(g) and (h) of this AD, could be installed during original aircraft 
manufacture, or during passenger to freighter modification. We expect 
that the actions specified in Boeing Alert Service Bulletin 727-
52A0151, dated February 12, 2016, can be accomplished on airplanes that 
are not identified in that service information. However, if an operator 
cannot accomplish the required actions in the service information due 
to the airplane configuration, or prefers to use different service 
information that is specific to their design, they can request an 
alternative method of compliance (AMOC) in accordance with paragraph 
(j) of this AD.

Request To Supersede AD 80-08-10 R1, Amendment 39-3830 (45 FR 46343, 
July 10, 1980) (``AD 80-08-10 R1'')

    Boeing requested that we revise the NPRM to supersede AD 80-08-10 
R1. Boeing stated that AD 80-08-10 R1 mandates MCD cam support 
assemblies having part numbers (P/Ns) 69-23588-1 and 69-23588-2 as 
specified in Boeing Service Bulletin 727-52A124. Boeing explained that 
the NPRM is adding cam support assemblies having P/Ns 69-23588-1 and 
69-23588-2 to the list in Boeing Alert Service Bulletin 727-52A0151, 
dated February 12, 2016. Boeing asserted that the addition of these 
components to the list of affected parts would mean that the operators 
have to perform high frequency eddy current inspection of cam support 
assemblies having P/Ns 69-23588-1 and 69-23588-2 as specified in AD 80-
08-10 R1 and perform ultrasonic inspection of the same components as 
specified in the NPRM. Boeing explained that cracking initiates at the 
bottom of the lubrication hole inside the cam support fitting lug and 
the cracking is not visible until it breaks to the surface of the lug. 
Therefore, the subsurface detection capability of the ultrasonic 
inspection provides a more reliable inspection.

[[Page 43172]]

    We partially agree with Boeing's request to supersede the 
inspections which are required by AD 80-08-10 R1. These inspections 
will overlap with the newly mandated repetitive inspections. We 
disagree with the request to revise this AD to supersede AD 80-08-10 
R1. Instead, we have added paragraph (i) to this AD to state that 
completion of the initial inspection and all applicable replacements 
required by paragraph (h) of this AD terminates all requirements of AD 
80-08-10 R1, for that airplane only. We have redesignated subsequent 
paragraphs accordingly.

Request To Revise Compliance Time

    Boeing requested that we revise paragraph (g)(1) of the proposed AD 
from ``before the accumulation of 18,000 total flight cycles'' to 
``before the accumulation of 18,000 door flight cycles. If the door 
flight cycles are not known, use total airplane flight cycles.'' Boeing 
explained that this change would provide relief for operators that have 
converted freighters by delaying the required inspection for the MCDs 
that have been in service less than 18,000 total door flight cycles, 
but are installed on the airplanes that have more than 18,000 total 
airframe flight cycles.
    We agree with Boeing's request. For the airplanes that have been 
converted to freighters, the compliance time for the initial inspection 
should be based on the number of cycles that the cam support assembly 
has been in service. We have revised paragraph (g)(1) of this AD 
accordingly.

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 727-52A0151, dated 
February 12, 2016. This service information describes procedures for an 
ultrasonic inspection of the cam support assemblies of the MCD 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.

Costs of Compliance

    We estimate that this AD will affect 45 airplanes of U.S. registry. 
We estimate the following costs to comply with this 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 per                    cycle.                 inspection cycle.
                              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 this 
replacement:

                                               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.
    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.

[[Page 43173]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-19-02 The Boeing Company: Amendment 39-19032; Docket No. FAA-
2016-9184; Product Identifier 2016-NM-060-AD.

(a) Effective Date

    This AD is effective October 19, 2017.

(b) Affected ADs

    This AD affects AD 80-08-10 R1, Amendment 39-3830 (45 FR 46343, 
July 10, 1980).

(c) Applicability

    This AD applies to The Boeing Company Model 727, 727C, 727-100, 
727-100C, 727-200, and 727-200F series airplanes, certificated in 
any category, equipped with a main cargo door (MCD).

(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 MCD 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 MCD could fail. We are issuing this AD to detect 
and correct cracking of the cam support assemblies of the MCD. Such 
cracking 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) 69-23588-1, 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 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 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 MCD 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 MCD; 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) Terminating Action for AD 80-08-10 R1, Amendment 39-3830 (45 FR 
46343, July 10, 1980)

    Accomplishment of the initial inspection and all applicable 
replacements required by paragraph (h) of this AD terminates all 
requirements of AD 80-08-10 R1, Amendment 39-3830 (45 FR 46343, July 
10, 1980), for that airplane only.

(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) 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

    For more information about this AD, contact Chandra Ramdoss, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO, 3960 
Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; 
fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this 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 727-52A0151, dated February 
12, 2016.
    (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 August 31, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-19441 Filed 9-13-17; 8:45 am]
 BILLING CODE 4910-13-P