82 FR 23500 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 98 (May 23, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 98 (May 23, 2017)
| Page Range | 23500-23504 | |
| FR Document | 2017-10259 |
[Federal Register Volume 82, Number 98 (Tuesday, May 23, 2017)] [Rules and Regulations] [Pages 23500-23504] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10259] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7426; Directorate Identifier 2015-NM-199-AD; Amendment 39-18900; AD 2017-11-01] 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 737-100, -200, and -200C series airplanes. This AD is intended to complete certain mandated programs to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires various repetitive inspections for cracking of certain lugs on the rear spar and horizontal stabilizer, related investigative and corrective actions if necessary, and replacement of the center section rear spar upper chord as applicable. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 27, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 27, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this 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 [[Page 23501]] and locating Docket No. FAA-2016-7426. 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- 7426; 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 AD, 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: George Garrido, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-5210; email: [email protected]. 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 certain The Boeing Company Model 737-100, -200, and -200C series airplanes. The NPRM published in the Federal Register on July 12, 2016 (81 FR 45075) (``the NPRM''). The NPRM was prompted by the need to complete certain mandated programs intended to support the airplane reaching its LOV of the engineering data that support the established structural maintenance program. The NPRM proposed to require repetitive detailed, high frequency eddy current (HFEC), and ultrasonic inspections of the center section rear spar upper clevis lugs and horizontal stabilizer rear spar upper lugs, as applicable, for any cracking, and related investigative and corrective actions if necessary. For certain airplanes, the NPRM also proposed to require replacement of the center section rear spar upper chord with a new part or a serviceable center section assembly. The NPRM also proposed to require repetitive HFEC and fluorescent dye penetrant inspections of the center section for cracking of the front and rear spar upper clevis lugs or horizontal stabilizer front and rear spar upper lugs, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking in the rear spar upper clevis lugs of the center section, and in the rear spar upper lugs of the horizontal stabilizer, which could result in the loss of structural integrity and controllability of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response. Request To Remove the Compliance Time Difference Boeing requested that we remove paragraph (o)(2) of the proposed AD, which specifies an exception to Boeing Alert Service Bulletin 737- 55A1033, Revision 2, dated August 7, 2015--the service information specifies a compliance time or repeat interval as ``Horizontal Stabilizer Center Section flight cycles'' or ``Horizontal Stabilizer flight cycles,'' and the proposed AD requires compliance for the corresponding time or repeat interval in airplane flight cycles. Boeing stated that the purpose of specifying horizontal stabilizer flight cycles and horizontal stabilizer center section flight cycles is to ensure that cycle accumulation is tracked to the component. Boeing also stated that the outboard horizontal stabilizer is contained in the ``replaceable'' structural components list and that it is possible to move the center section of the horizontal stabilizer to another airplane of the same type design without any rework to the component. Boeing commented that as the fleet ages and airplanes are transferred among operators, used components will be more prevalent, and it is therefore necessary to track the replaceable component flight cycles accumulated after the AD date. Boeing also stated that the compliance times are subsequent to the later of the compliance time specified in Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, or the date of the spar chord replacement (horizontal stabilizer or center section as applicable) with a new spar chord. Boeing commented that for airplanes on which the age of parts is not known, the compliance time defaults to being subsequent to Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, and are therefore, enforceable as stated, and that likewise, the repetitive intervals must follow the component after transfer. Boeing stated that since the repetitive inspection interval is subsequent to the previous inspection specified in Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, there are no circumstances where the operator will be unable to identify those incremental cycles on the component. We agree with the commenter's request. It is possible to replace the horizontal stabilizer and/or the horizontal stabilizer center section on one Model 737-100, -200, or -200C series airplane (``Model 737CL airplane'') with that from another airplane. The limited information available suggests that a center section has been replaced on at least one Model 737CL airplane, and numerous horizontal stabilizers have been replaced. If a major structural element such as the horizontal stabilizer or the horizontal stabilizer center section is moved from one airplane to a different airplane, the hours and cycles that the part has accumulated should be tracked separately from the airplane flight cycles and flight hours. Boeing has published Service Letter 737-SL-05-019, dated November 23, 2016, which lists Removable Structural Components (RSC) for Model 737-200, 737-200C, 737-300, 737-400, and 737-500 series airplanes in accordance with Air Transport Association (ATA) Specification 120. That list does include some parts from the horizontal stabilizer and the horizontal stabilizer center section. In order to make sure that cycle accumulation is tracked to the component, we have removed paragraph (o)(2) of the proposed AD from this AD. We have also redesignated paragraph (o)(1) of the proposed AD as paragraph (o) of this AD. Clarification of Terminating Actions We have revised paragraph (q)(1) of this AD to clarify that accomplishing the initial inspections specified in paragraph (g) of this AD terminates all requirements of AD 84-23-05, Amendment 39-4949 (Docket No. 84-NM-37-AD; 49 FR 45744, November 20, 1984). We have revised paragraph (q)(2) of this AD to clarify that accomplishing the initial inspections specified in paragraphs (m) and (n) of this AD terminates all requirements of AD 86-12-05, Amendment 39-5321 (Docket No. 85-NM-162-AD; 51 FR 18771, May 22, 1986). Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes: [[Page 23502]]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 AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. The service information describes procedures for repetitive detailed, HFEC, and ultrasonic inspections for cracking of the center section rear spar upper clevis lugs and rear spar upper lugs of the horizontal stabilizer; repetitive HFEC and fluorescent dye penetrant inspections for cracking in the front and rear spar upper clevis lugs of the center section and the front and rear spar upper lugs of the horizontal stabilizer; and related investigative and corrective actions. For certain airplanes, the service information describes procedures for replacement of the center section rear spar upper chord with a new part and replacing the center section with a serviceable center section assembly, or installing bushings and sleeves, as applicable. 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 affects 84 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 ---------------------------------------------------------------------------------------------------------------- Repetitive detailed, HFEC, and 9 work-hours x $85 per $0 $765 per $64,260 per ultrasonic inspections. hour = $765 per inspection cycle. inspection cycle. inspection cycle. Repetitive HFEC and fluorescent 118 work-hours x $85 0 $10,030 per $842,520 per dye penetrant inspections. per hour = $10,030 per inspection cycle. inspection cycle. inspection cycle. Replacement.................... Up to 252 work-hours x 25,000 Up to $46,420 per Up to $3,899,280 $85 per hour = $21,420 inspection cycle. per inspection per inspection cycle. cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary inspections, repairs, and replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these inspections, repairs, and replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Bolt and Bushing Removal/Inspection, 101 work-hours x $85 per $0 $8,585. Fabrication, and Installation. hour = $8,585. Repair and replacement................. Up to 252 work-hours x 25,000 Up to $46,420. $85 per hour = $21,420. ---------------------------------------------------------------------------------------------------------------- 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 This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: 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): 2017-11-01 The Boeing Company: Amendment 39-18900; Docket No. [[Page 23503]] FAA-2016-7426; Directorate Identifier 2015-NM-199-AD. (a) Effective Date This AD is effective June 27, 2017. (b) Affected ADs This AD affects AD 84-23-05, Amendment 39-4949 (Docket No. 84- NM-37-AD; 49 FR 45744, November 20, 1984); and AD 86-12-05, Amendment 39-5321 (Docket No. 85-NM-162-AD; 51 FR 18771, May 22, 1986). (c) Applicability This AD applies to The Boeing Company Model 737-100, -200, and - 200C series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to detect and correct cracking in the rear spar upper clevis lugs of the center section, and in the rear spar upper lugs of the horizontal stabilizer, which could result in the loss of structural integrity and controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections, Related Investigative and Corrective Actions (Service Information Tables 1 and 3) At the applicable time specified in table 1 or table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD: Do detailed, high frequency eddy current (HFEC), and ultrasonic inspections of the center section rear spar upper clevis lugs for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 55A1033, Revision 2, dated August 7, 2015; except as specified in paragraph (p) of this AD. Do all related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 1 or table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (h) Replacement (Service Information Table 1) For airplanes identified as Group 1, Configuration 1, in Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015: At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD, replace the center section rear upper chord with a new part or replace the center section with a serviceable center section assembly, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (i) Repetitive Post-Replacement Inspections, Related Investigative and Corrective Actions (Service Information Table 2) For airplanes identified as Group 1, Configuration 1, in Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, with a new or serviceable 0.932-inch-thick center section rear spar upper chord: At the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD, do detailed, HFEC, and ultrasonic inspections of the center section rear spar upper chord clevis lugs for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015; except as specified in paragraph (p) of this AD. Do all related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (j) Post-Replacement Inspections, Related Investigative and Corrective Actions (Service Information Table 4) For airplanes on which the center section rear spar upper chord was last replaced with a new part or serviceable part: Within the applicable times specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD, do detailed, HFEC, and ultrasonic inspections of the center section rear spar upper chord clevis lugs for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015; except as specified in paragraph (p) of this AD. Do all related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 4 of 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (k) Repetitive Inspections, Related Investigative and Corrective Actions of the Horizontal Stabilizer (Service Information Table 5) Within the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD, do detailed, HFEC, and ultrasonic inspections of the rear spar upper lugs of the horizontal stabilizer for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015; except as specified in paragraph (p) of this AD. Do all related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 5 of 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (l) Post Replacement Inspections, Related Investigative and Corrective Actions (Service Information Table 6) For airplanes with a replaced horizontal stabilizer with a new part or serviceable assembly, within the applicable times specified in table 6 of 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD: Do a detailed, HFEC, and ultrasonic inspection of the rear spar upper lugs of the horizontal stabilizer for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015; except as specified in paragraph (p) of this AD. Do all related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 6 of 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (m) Scheduled Inspections, Related Investigative and Corrective Actions (Service Information Table 7) Within the applicable times specified in table 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD: Do HFEC and fluorescent dye penetrant inspections for cracking in the front and rear spar upper clevis lugs of the center section and front and rear spar upper lugs of the horizontal stabilizer, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015; except as specified in paragraph (p) of this AD. Do all related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (n) Post Scheduled Inspections, Related Investigative and Corrective Actions (Service Information Table 8) For airplanes on which the center section rear spar upper chord or horizontal stabilizer rear spar upper chord has been replaced: Within the applicable time specified in table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, except as specified in paragraph (o) of this AD; do HFEC and fluorescent dye penetrant [[Page 23504]] inspections for cracking in the front and rear spar upper clevis lugs of the center section or front and rear spar upper lugs of the horizontal stabilizer, as applicable, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 55A1033, Revision 2, dated August 7, 2015; except as specified in paragraph (p) of this AD. Do all related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015. (o) Exceptions to the Service Information: Compliance Times Where Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, specifies a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (p) Exception to the Service Information: Repair Compliance Method If any cracking of the lug is found during any inspection required by this AD, and Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, specifies to contact Boeing for appropriate action: Before further flight, repair the lug using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (q) Terminating Actions (1) For Model 737-100, -200, and -200C series airplanes: Accomplishment of the initial inspections specified in paragraph (g) of this AD terminates all requirements of AD 84-23-05, Amendment 39- 4949 (Docket No. 84-NM-37-AD; 49 FR 45744, November 20, 1984). (2) For Model 737-200 and -200C series airplanes: Accomplishment of the initial inspections specified in paragraph (m) and (n) of this AD terminates all requirements of AD 86-12-05, Amendment 39- 5321 (Docket No. 85-NM-162-AD; 51 FR 18771, May 22, 1986). (r) 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 (s) of this AD. (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. (s) Related Information For more information about this AD, contact George Garrido, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-5210; email: [email protected]. (t) 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 737-55A1033, Revision 2, dated August 7, 2015. (ii) Reserved. (3) For Boeing 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 Airplane Directorate, 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 May 12, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10259 Filed 5-22-17; 8:45 am] BILLING CODE 4910-13-P
![23500 Federal Register / Vol. 82, No. 98 / Tuesday, May 23, 2017 / Rules and Regulations
effective date of this AD), whichever occurs instructions, completing and reviewing the Issued in Kansas City, Missouri, on May 9,
later. Repetitively thereafter inspect every collection of information. All responses to 2017.
120 hours TIS until the nacelle fitting has this collection of information are mandatory. Melvin Johnson,
reached 7,500 hours TIS. When the airplane Comments concerning the accuracy of this Acting Manager, Small Airplane Directorate,
reaches 7,500 hours TIS on the affected burden and suggestions for reducing the Aircraft Certification Service.
nacelle fitting, the repetitive inspection time burden should be directed to the FAA at: 800
must be changed to 60 hours TIS. A 10-hour [FR Doc. 2017–10391 Filed 5–22–17; 8:45 am]
Independence Ave. SW., Washington, DC
TIS grace period is allowed for those BILLING CODE 4910–13–P
20591, Attn: Information Collection
airplanes between 51 and 110 hours TIS for
Clearance Officer, AES–200.
the first repetitive inspection when the
airplane reaches 7,500 hours TIS on the (l) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION
nacelle. (AMOCs)
(2) For airplanes with 7,400 hours TIS or Federal Aviation Administration
(1) The Manager, Wichita ACO, FAA, has
more on the affected nacelle fitting: Before or
upon accumulating 7,500 hours TIS on the the authority to approve AMOCs for this AD,
if requested using the procedures found in 14 14 CFR Part 39
nacelle fitting or within the next 25 hours
TIS after June 7, 2017 (the effective date of CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector [Docket No. FAA–2016–7426; Directorate
this AD), whichever occurs later. Repetitively
or local Flight Standards District Office, as Identifier 2015–NM–199–AD; Amendment
thereafter inspect every 60 hours TIS.
appropriate. If sending information directly 39–18900; AD 2017–11–01]
(h) Replacement to the manager of the ACO, send it to the
(1) If cracks are found during any attention of the person identified in RIN 2120–AA64
inspection required in paragraph (g) of this paragraph (m) of this AD.
AD, before further flight, replace the cracked (2) Before using any approved AMOC, Airworthiness Directives; The Boeing
nacelle fitting. notify your appropriate principal inspector, Company Airplanes
(2) If a cracked nacelle fitting P/N or lacking a principal inspector, the manager
5292029–9, 5292029–10, 5292029–11, AGENCY: Federal Aviation
of the local flight standards district office/
5292029–12, 5292029–21, 5292029–22, Administration (FAA), DOT.
certificate holding district office.
5292029–23, or 5292029–24, is replaced with ACTION: Final rule.
a new nacelle fitting P/N 5292029–9, (m) Related Information
5292029–10, 5292029–11, 5292029–12, SUMMARY: We are adopting a new
For more information about this AD,
5292029–21, 5292029–22, 5292029–23, or airworthiness directive (AD) for certain
contact Paul Chapman, Aerospace Engineer,
5292029–24, the new part is subject to the The Boeing Company Model 737–100,
requirements of this AD. Wichita ACO, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946– –200, and –200C series airplanes. This
(i) Reporting Requirement 4152; fax: (316) 946–4107; email: AD is intended to complete certain
Within 10 days after doing the initial paul.chapman@faa.gov or Wichita-COS@ mandated programs to support the
inspection in paragraph (g) of this AD or faa.gov. airplane reaching its limit of validity
within 10 days after June 7, 2017 (the (LOV) of the engineering data that
(n) Material Incorporated by Reference
effective date of this AD), whichever occurs support the established structural
later, using the Attachment to Textron (1) The Director of the Federal Register maintenance program. This AD requires
Aviation Mandatory Multi-engine Service approved the incorporation by reference
various repetitive inspections for
Letter MEL–54–02, Revision 2, dated March (IBR) of the service information listed in this
29, 2017, ‘‘Visual Inspection Results Form,’’ paragraph under 5 U.S.C. 552(a) and 1 CFR
cracking of certain lugs on the rear spar
complete the report and send a copy to the part 51. and horizontal stabilizer, related
Wichita Aircraft Certification Office (ACO) at (2) You must use this service information investigative and corrective actions if
the address listed in paragraph (m) of this AD as applicable to do the actions required by necessary, and replacement of the center
or by email to Wichita-COS@faa.gov. this AD, unless this AD specifies otherwise. section rear spar upper chord as
(j) Credit for Actions Accomplished in (i) Textron Aviation Mandatory Multi- applicable. We are issuing this AD to
Accordance With Previous Service engine Service Letter MEL–54–02, Revision address the unsafe condition on these
Information 2, dated March 29, 2017. products.
This AD allows credit for the inspections (ii) Reserved.
DATES: This AD is effective June 27,
required in paragraph (g) of this AD if done (3) For Textron Aviation Inc. service
information identified in this AD, contact
2017.
before June 7, 2017 (the effective date of this The Director of the Federal Register
AD), following Textron Aviation Mandatory Textron Aviation Inc., Textron Aviation
Customer Service, One Cessna Blvd., approved the incorporation by reference
Multi-engine Service Letter MEL–54–02,
dated December 23, 2016, or Textron Wichita, KS 67215; telephone: (316) 517– of a certain publication listed in this AD
Aviation Mandatory Multi-engine Service 5800; email: corpcom@txtav.comm; Internet: as of June 27, 2017.
Letter MEL–54–02, Revision 1, dated March www.txtav.com. ADDRESSES: For service information
22, 2017. (4) You may view this service information identified in this final rule, contact
(k) Paperwork Reduction Act Burden at the FAA, Small Airplane Directorate, 901 Boeing Commercial Airplanes,
Statement Locust, Kansas City, Missouri 64106. For Attention: Contractual & Data Services
information on the availability of this (C&DS), 2600 Westminster Blvd., MC
A federal agency may not conduct or material at the FAA, call (816) 329–4148. It
sponsor, and a person is not required to 110–SK57, Seal Beach, CA 90740–5600;
is also available on the internet at http://
respond to, nor shall a person be subject to telephone 562–797–1717; Internet
www.regulations.gov by searching for and
a penalty for failure to comply with a https://www.myboeingfleet.com. You
locating Docket No. FAA–2017–0450.
collection of information subject to the may view this referenced service
(5) You may view this service information
jstallworth on DSK7TPTVN1PROD with RULES
requirements of the Paperwork Reduction information at the FAA, Transport
Act unless that collection of information that is incorporated by reference at the
National Archives and Records Airplane Directorate, 1601 Lind Avenue
displays a current valid OMB Control
Number. The OMB Control Number for this Administration (NARA). For information on SW., Renton, WA. For information on
information collection is 2120–0056. Public the availability of this material at NARA, call the availability of this material at the
reporting for this collection of information is 202–741–6030, or go to: http:// FAA, call 425–227–1221. It is also
estimated to be approximately 5 minutes per www.archives.gov/federal-register/cfr/ibr- available on the Internet at http://
response, including the time for reviewing locations.html. www.regulations.gov by searching for
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![23502 Federal Register / Vol. 82, No. 98 / Tuesday, May 23, 2017 / Rules and Regulations
• Are consistent with the intent that information describes procedures for new part and replacing the center
was proposed in the NPRM for repetitive detailed, HFEC, and section with a serviceable center section
correcting the unsafe condition; and ultrasonic inspections for cracking of assembly, or installing bushings and
• Do not add any additional burden the center section rear spar upper clevis sleeves, as applicable. This service
upon the public than was already lugs and rear spar upper lugs of the information is reasonably available
proposed in the NPRM. horizontal stabilizer; repetitive HFEC because the interested parties have
We also determined that these and fluorescent dye penetrant access to it through their normal course
changes will not increase the economic inspections for cracking in the front and of business or by the means identified
burden on any operator or increase the rear spar upper clevis lugs of the center in the ADDRESSES section.
scope of this AD. section and the front and rear spar
upper lugs of the horizontal stabilizer; Costs of Compliance
Related Service Information Under 1 and related investigative and corrective
CFR Part 51 actions. For certain airplanes, the We estimate that this AD affects 84
We reviewed Boeing Alert Service service information describes airplanes of U.S. registry.
Bulletin 737–55A1033, Revision 2, procedures for replacement of the center We estimate the following costs to
dated August 7, 2015. The service section rear spar upper chord with a comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Repetitive detailed, HFEC, and ultra- 9 work-hours × $85 per hour = $765 $0 $765 per inspection $64,260 per inspec-
sonic inspections. per inspection cycle. cycle. tion cycle.
Repetitive HFEC and fluorescent dye 118 work-hours × $85 per hour = 0 $10,030 per inspec- $842,520 per in-
penetrant inspections. $10,030 per inspection cycle. tion cycle. spection cycle.
Replacement .......................................... Up to 252 work-hours × $85 per hour = 25,000 Up to $46,420 per Up to $3,899,280
$21,420 per inspection cycle. inspection cycle. per inspection
cycle.
We estimate the following costs to do based on the results of the inspection. number of aircraft that might need these
any necessary inspections, repairs, and We have no way of determining the inspections, repairs, and replacements:
replacements that would be required
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Bolt and Bushing Removal/Inspection, Fabrication, 101 work-hours × $85 per hour = $8,585 .................... $0 $8,585.
and Installation.
Repair and replacement ............................................... Up to 252 work-hours × $85 per hour = $21,420 ........ 25,000 Up to $46,420.
Authority for This Rulemaking Regulatory Findings List of Subjects in 14 CFR Part 39
Title 49 of the United States Code This AD will not have federalism Air transportation, Aircraft, Aviation
specifies the FAA’s authority to issue implications under Executive Order safety, Incorporation by reference,
rules on aviation safety. Subtitle I, 13132. This AD will not have a Safety.
section 106, describes the authority of substantial direct effect on the States, on
the relationship between the national Adoption of the Amendment
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more government and the States, or on the Accordingly, under the authority
detail the scope of the Agency’s distribution of power and delegated to me by the Administrator,
authority. responsibilities among the various the FAA amends 14 CFR part 39 as
levels of government. follows:
We are issuing this rulemaking under
For the reasons discussed above, I
the authority described in Subtitle VII, PART 39—AIRWORTHINESS
certify that this AD:
Part A, Subpart III, Section 44701: DIRECTIVES
‘‘General requirements.’’ Under that (1) Is not a ‘‘significant regulatory
section, Congress charges the FAA with action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under ■ 1. The authority citation for part 39
promoting safe flight of civil aircraft in continues to read as follows:
air commerce by prescribing regulations DOT Regulatory Policies and Procedures
for practices, methods, and procedures (44 FR 11034, February 26, 1979), Authority: 49 U.S.C. 106(g), 40113, 44701.
jstallworth on DSK7TPTVN1PROD with RULES
the Administrator finds necessary for (3) Will not affect intrastate aviation § 39.13 [Amended]
safety in air commerce. This regulation in Alaska, and
is within the scope of that authority (4) Will not have a significant ■ 2. The FAA amends § 39.13 by adding
because it addresses an unsafe condition economic impact, positive or negative, the following new airworthiness
that is likely to exist or develop on on a substantial number of small entities directive (AD):
products identified in this rulemaking under the criteria of the Regulatory 2017–11–01 The Boeing Company:
action. Flexibility Act. Amendment 39–18900; Docket No.
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![23504 Federal Register / Vol. 82, No. 98 / Tuesday, May 23, 2017 / Rules and Regulations
inspections for cracking in the front and rear Designation Authorization (ODA) that has ACTION: Final rule.
spar upper clevis lugs of the center section been authorized by the Manager, Los Angeles
or front and rear spar upper lugs of the ACO, to make those findings. To be SUMMARY: We are adopting a new
horizontal stabilizer, as applicable, and do all approved, the repair method, modification airworthiness directive (AD) for all The
applicable related investigative and deviation, or alteration deviation must meet Boeing Company Model MD–90–30
corrective actions, in accordance with the the certification basis of the airplane and the airplanes. This AD was prompted by a
Accomplishment Instructions of Boeing Alert approval must specifically refer to this AD.
report of cracking in a horizontal
Service Bulletin 737–55A1033, Revision 2,
(s) Related Information stabilizer rear spar cap. This AD
dated August 7, 2015; except as specified in
paragraph (p) of this AD. Do all related For more information about this AD, requires repetitive inspections for any
investigative and corrective actions before contact George Garrido, Aerospace Engineer, crack in the left and right side
further flight. Repeat the inspections Airframe Branch, ANM–120L, FAA, Los horizontal stabilizer rear spar upper
thereafter at the applicable times specified in Angeles Aircraft Certification Office (ACO), caps, and repair or replacement if
table 8 of paragraph 1.E., ‘‘Compliance,’’ of 3960 Paramount Boulevard, Lakewood, CA
necessary. We are issuing this AD to
Boeing Alert Service Bulletin 737–55A1033, 90712–4137; phone: 562–627–5232; fax: 562–
627–5210; email: George.Garrido@faa.gov. address the unsafe condition on these
Revision 2, dated August 7, 2015.
products.
(o) Exceptions to the Service Information: (t) Material Incorporated by Reference
DATES: This AD is effective June 27,
Compliance Times (1) The Director of the Federal Register
2017.
Where Boeing Alert Service Bulletin 737– approved the incorporation by reference
(IBR) of the service information listed in this
The Director of the Federal Register
55A1033, Revision 2, dated August 7, 2015, approved the incorporation by reference
specifies a compliance time ‘‘after the paragraph under 5 U.S.C. 552(a) and 1 CFR
Revision 2 date of this service bulletin,’’ this part 51. of a certain publication listed in this AD
AD requires compliance within the specified (2) You must use this service information as of June 27, 2017.
compliance time after the effective date of as applicable to do the actions required by ADDRESSES: For service information
this AD. this AD, unless the AD specifies otherwise. identified in this final rule, contact
(i) Boeing Alert Service Bulletin 737–
(p) Exception to the Service Information: Boeing Commercial Airplanes,
55A1033, Revision 2, dated August 7, 2015.
Repair Compliance Method (ii) Reserved. Attention: Contractual & Data Services
(3) For Boeing service information (C&DS), 2600 Westminster Blvd., MC
If any cracking of the lug is found during
any inspection required by this AD, and identified in this AD, contact Boeing 110–SK57, Seal Beach, CA 90740–5600;
Boeing Alert Service Bulletin 737–55A1033, Commercial Airplanes, Attention: telephone 562–797–1717; Internet
Revision 2, dated August 7, 2015, specifies to Contractual & Data Services (C&DS), 2600 https://www.myboeingfleet.com. You
contact Boeing for appropriate action: Before Westminster Blvd., MC 110–SK57, Seal may view this referenced service
further flight, repair the lug using a method Beach, CA 90740–5600; telephone 562–797– information at the FAA, Transport
approved in accordance with the procedures 1717; Internet https:// Airplane Directorate, 1601 Lind Avenue
specified in paragraph (r) of this AD. www.myboeingfleet.com.
(4) You may view this service information SW., Renton, WA. For information on
(q) Terminating Actions at the FAA, Transport Airplane Directorate, the availability of this material at the
(1) For Model 737–100, –200, and –200C 1601 Lind Avenue SW., Renton, WA. For FAA, call 425–227–1221. It is also
series airplanes: Accomplishment of the information on the availability of this available on the Internet at http://
initial inspections specified in paragraph (g) material at the FAA, call 425–227–1221. www.regulations.gov by searching for
of this AD terminates all requirements of AD (5) You may view this service information and locating Docket No. FAA–2016–
84–23–05, Amendment 39–4949 (Docket No. that is incorporated by reference at the 9433.
84–NM–37–AD; 49 FR 45744, November 20, National Archives and Records
1984). Administration (NARA). For information on Examining the AD Docket
(2) For Model 737–200 and –200C series the availability of this material at NARA, call
202–741–6030, or go to: http://
You may examine the AD docket on
airplanes: Accomplishment of the initial
inspections specified in paragraph (m) and www.archives.gov/federal-register/cfr/ibr- the Internet at http://
(n) of this AD terminates all requirements of locations.html. www.regulations.gov by searching for
AD 86–12–05, Amendment 39–5321 (Docket and locating Docket No. FAA–2016–
Issued in Renton, Washington, on May 12,
No. 85–NM–162–AD; 51 FR 18771, May 22, 2017.
9433; or in person at the Docket
1986). Management Facility between 9 a.m.
Michael Kaszycki,
(r) Alternative Methods of Compliance and 5 p.m., Monday through Friday,
Acting Manager, Transport Airplane
(AMOCs) except Federal holidays. The AD docket
Directorate, Aircraft Certification Service.
contains this AD, the regulatory
(1) The Manager, Los Angeles Aircraft [FR Doc. 2017–10259 Filed 5–22–17; 8:45 am]
Certification Office (ACO), FAA, has the evaluation, any comments received, and
BILLING CODE 4910–13–P other information. The address for the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14 Docket Office (phone: 800–647–5527) is
CFR 39.19. In accordance with 14 CFR 39.19, Docket Management Facility, U.S.
send your request to your principal inspector DEPARTMENT OF TRANSPORTATION
Department of Transportation, Docket
or local Flight Standards District Office, as Operations, M–30, West Building
appropriate. If sending information directly Federal Aviation Administration
Ground Floor, Room W12–140, 1200
to the manager of the ACO, send it to the
14 CFR Part 39 New Jersey Avenue SE., Washington,
attention of the person identified in
paragraph (s) of this AD. DC 20590.
[Docket No. FAA–2016–9433; Directorate FOR FURTHER INFORMATION CONTACT:
(2) Before using any approved AMOC, Identifier 2016–NM–159–AD; Amendment
notify your appropriate principal inspector, 39–18901; AD 2017–11–02] James Guo, Aerospace Engineer,
jstallworth on DSK7TPTVN1PROD with RULES
or lacking a principal inspector, the manager Airframe Branch, ANM–120L, FAA, Los
of the local flight standards district office/ RIN 2120–AA64 Angeles Aircraft Certification Office
certificate holding district office. (ACO), 3960 Paramount Boulevard,
(3) An AMOC that provides an acceptable Airworthiness Directives; The Boeing
level of safety may be used for any repair,
Lakewood, CA 90712–4137; phone:
Company Airplanes 562–627–5357; fax: 562–627–5210;
modification, or alteration required by this
AD if it is approved by the Boeing AGENCY:Federal Aviation email: james.guo@faa.gov.
Commercial Airplanes Organization Administration (FAA), DOT. SUPPLEMENTARY INFORMATION:
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Document Created: 2017-05-23 02:14:39
Document Modified: 2017-05-23 02:14:39
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective June 27, 2017. | |
| Contact | George Garrido, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 82 FR 23500 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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