81 FR 45075 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 133 (July 12, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 133 (July 12, 2016)
| Page Range | 45075-45079 | |
| FR Document | 2016-16322 |
[Federal Register Volume 81, Number 133 (Tuesday, July 12, 2016)] [Proposed Rules] [Pages 45075-45079] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-16322] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7426; Directorate Identifier 2015-NM-199-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 certain The Boeing Company Model 737-100, -200, and -200C series airplanes. This proposed 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. This proposed AD would 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, this proposed AD would require replacement of the center section rear spar upper chord with a new part and a serviceable center section assembly. This proposed AD would also 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 proposing 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. DATES: We must receive comments on this proposed AD by August 26, 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 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- 7426. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for [[Page 45076]] 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 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: Payman Soltani, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627-5210; email: [email protected]. 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-2016-7426; Directorate Identifier 2015-NM-199-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 As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs have been developed to support initiatives that will ensure the continued airworthiness of aging airplane structure. The last element of those initiatives is the requirement to establish a LOV of the engineering data that support the structural maintenance program under 14 CFR 26.21. This proposed AD is the result of an assessment of the previously established programs by the DAH during the process of establishing the LOV for the affected airplanes. The actions specified in this proposed AD are necessary to complete certain programs to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its LOV of the engineering data that support the established structural maintenance program. An operator detected a cracked center section at the rear spar upper chord clevis lug. This condition, if not corrected, could result in cracking in the rear spar clevis lugs of the horizontal stabilizer center section, which could result in loss of structural integrity and controllability of the airplane. 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 of the center section rear spar upper clevis lugs and rear spar upper lugs of the horizontal stabilizer; 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. 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. 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-2016-7426. The phrase ``related investigative actions'' is used in this NPRM. Related investigative actions are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is also used in this NPRM. Corrective actions are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, specifies to contact the manufacturer for certain instructions, but this proposed AD would require accomplishment of repair methods, modification deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Where Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, specifies a compliance time or repeat interval as ``Horizontal Stabilizer Center Section flight cycles'' or ``Horizontal Stabilizer flight cycles,'' this AD requires compliance for the corresponding time or repeat interval in airplane flight cycles. Costs of Compliance We estimate that this proposed AD affects 84 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Parts Cost on U.S. Action Labor cost cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Repetitive detailed, HFEC, and 9 work-hours x $85 $0 $765 per inspection $64,260 per ultrasonic inspections. per hour = $765 per cycle. inspection cycle. inspection cycle. [[Page 45077]] Repetitive HFEC and fluorescent 118 work-hours x $85 0 $10,030 per $842,520 per dye penetrant inspections. per hour = $10,030 inspection cycle. inspection cycle. per inspection cycle. Replacement....................... Up to 252 25,000 Up to $46,420 per Up to $3,899,280 per work[dash]hours x inspection cycle. inspection cycle. $85 per hour = $21,420 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary inspections, repairs, and 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 these inspections, repairs, and replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Bolt and Bushing Removal/ 101 work-hours x $85 $0 $8,585. Inspection, Fabrication, and per hour = $8,585. Installation. Repair and replacement............. Up to 252 25,000 Up to $46,420 per inspection cycle. work[dash]hours x $85 per hour = $21,420 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- 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-2016-7426; Directorate Identifier 2015-NM-199-AD. (a) Comments Due Date We must receive comments by August 26, 2016. (b) Affected ADs This AD affects AD 84-23-05, Amendment 39-4949 (49 FR 45744, November 20, 1984); and AD 86-12-05, Amendment 39-5321 (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 proposed 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 [[Page 45078]] 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 or serviceable part, 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 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 (1) 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. (2) Where Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015, specifies a compliance time or repeat interval as ``Horizontal Stabilizer Center Section flight cycles'' or ``Horizontal Stabilizer flight cycles,'' this AD requires compliance for the corresponding time or repeat interval in airplane flight cycles. (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 inspections specified in paragraph (g) of this AD terminates the requirements of paragraph A. of AD 84-23-05, Amendment 39-4949 (49 FR 45744, November 20, 1984). (2) For Model 737-200 and -200C series airplanes: Accomplishment of the inspections specified in paragraph (m) and (n) of this AD terminates the requirements of paragraphs A. and B. of AD 86-12-05, Amendment 39-5321 (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 [[Page 45079]] attention of the person identified in paragraph (s)(1) 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 (1) For more information about this AD, contact Payman Soltani, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5313; fax: 562-627-5210; email: [email protected]. (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 June 28, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-16322 Filed 7-11-16; 8:45 am] BILLING CODE 4910-13-P
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(2) For airplanes with an extended wing tip standards district office/certificate holding high frequency eddy current (HFEC),
that has been modified using Saab Service district office. The AMOC approval letter and ultrasonic inspections of the center
Bulletin 340–27–099: Deactivate the stall must specifically reference this AD. section rear spar upper clevis lugs and
speed curves in the SWC having P/N (2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
horizontal stabilizer rear spar upper
0020AK7.
actions from a manufacturer, the action must lugs, as applicable, for any cracking, and
(h) Replacement of SWCs be accomplished using a method approved related investigative and corrective
Within 3 months after the effective date of by the Manager, International Branch, ANM– actions if necessary. For certain
this AD: Do the replacement specified in 116, Transport Airplane Directorate, FAA; or airplanes, this proposed AD would
paragraph (h)(1) or (h)(2) of this AD, as the European Aviation Safety Agency require replacement of the center
applicable. (EASA); or Saab AB, Saab Aeronautics’ EASA section rear spar upper chord with a
(1) For airplanes with basic wing tips: Design Organization Approval (DOA). If new part and a serviceable center
Replace all SWCs with new, improved SWCs approved by the DOA, the approval must
having P/N 0020AK6–1, in accordance with include the DOA-authorized signature.
section assembly. This proposed AD
the Accomplishment Instructions of Saab would also require repetitive HFEC and
Service Bulletin 340–27–121, dated July 11, (l) Related Information fluorescent dye penetrant inspections of
2014. (1) Refer to Mandatory Continuing the center section for cracking of the
(2) For airplanes with extended wing tips: Airworthiness Information (MCAI) EASA front and rear spar upper clevis lugs or
Replace all SWCs with new, improved SWCs Airworthiness Directive 2014–0218, dated horizontal stabilizer front and rear spar
having P/N 0020AK7–1, in accordance with September 29, 2014, for related information. upper lugs, and related investigative
the Accomplishment Instructions of Saab This MCAI may be found in the AD docket
and corrective actions if necessary. We
Service Bulletin 340–27–122, dated July 11, on the Internet at http://www.regulations.gov
2014. by searching for and locating Docket No. are proposing this AD to detect and
FAA–2015–6544. correct cracking in the rear spar upper
(i) Concurrent Modification (2) For service information identified in clevis lugs of the center section, and in
Before or concurrently with the this AD, contact Saab AB, Saab Aeronautics, the rear spar upper lugs of the
accomplishment of the applicable SE–581 88, Linköping, Sweden; telephone horizontal stabilizer which could result
requirements of paragraph (h) of this AD, do +46 13 18 5591; fax +46 13 18 4874; email in the loss of structural integrity and
the actions specified in paragraph (i)(1) or saab340.techsupport@saabgroup.com; controllability of the airplane.
(i)(2) of this AD, as applicable to airplane Internet http://www.saabgroup.com. You
configuration. DATES: We must receive comments on
may view this service information at the
(1) For airplanes on which either Saab AB FAA, Transport Airplane Directorate, 1601 this proposed AD by August 26, 2016.
Mod No. 2650 or Mod No. 2859 is not Lind Avenue SW., Renton, WA. For ADDRESSES: You may send comments,
installed: Modify the stall warning and information on the availability of this using the procedures found in 14 CFR
identification system, in accordance with the material at the FAA, call 425–227–1221. 11.43 and 11.45, by any of the following
Accomplishment Instructions of Saab Service
Bulletin 340–27–120, dated July 11, 2014. Issued in Renton, Washington, on June 23, methods:
(2) For airplanes on which either Saab AB 2016. • Federal eRulemaking Portal: Go to
Mod No. 2650 or Mod No. 2859 is installed, Dorr M. Anderson, http://www.regulations.gov. Follow the
or on which both mods are installed: Modify Acting Manager, Transport Airplane instructions for submitting comments.
the stall warning and identification system, Directorate, Aircraft Certification Service. • Fax: 202–493–2251.
in accordance with the Accomplishment
[FR Doc. 2016–15927 Filed 7–11–16; 8:45 am] • Mail: U.S. Department of
Instructions of Saab Service Bulletin 340–27– Transportation, Docket Operations, M–
109, dated April 14, 2014. BILLING CODE 4910–13–P
30, West Building Ground Floor, Room
(j) Parts Installation Prohibitions W12–140, 1200 New Jersey Avenue SE.,
After the replacement required by DEPARTMENT OF TRANSPORTATION Washington, DC 20590.
paragraph (h) of this AD, no person may • Hand Delivery: Deliver to Mail
install any SWC having P/N 0020AK, Federal Aviation Administration address above between 9 a.m. and 5
0020AK1, 0020AK2, 0020AK4, 0020AK6, p.m., Monday through Friday, except
0020AK7, or 0020AK3 MOD 1, on any 14 CFR Part 39 Federal holidays.
airplane. For service information identified in
[Docket No. FAA–2016–7426; Directorate
(k) Other FAA AD Provisions Identifier 2015–NM–199–AD] this NPRM, contact Boeing Commercial
The following provisions also apply to this Airplanes, Attention: Data & Services
AD: RIN 2120–AA64 Management, P. O. Box 3707, MC 2H–
(1) Alternative Methods of Compliance 65, Seattle, WA 98124–2207; telephone:
(AMOCs): The Manager, International Airworthiness Directives; The Boeing 206–544–5000, extension 1; fax: 206–
Branch, ANM–116, Transport Airplane Company Airplanes 766–5680; Internet: https://
Directorate, FAA, has the authority to www.myboeingfleet.com. You may view
AGENCY: Federal Aviation
approve AMOCs for this AD, if requested this referenced service information at
using the procedures found in 14 CFR 39.19. Administration (FAA), DOT.
In accordance with 14 CFR 39.19, send your ACTION: Notice of proposed rulemaking the FAA, Transport Airplane
request to your principal inspector or local (NPRM). Directorate, 1601 Lind Avenue SW.,
Flight Standards District Office, as Renton, WA. For information on the
appropriate. If sending information directly SUMMARY: We propose to adopt a new availability of this material at the FAA,
to the International Branch, send it to ATTN: airworthiness directive (AD) for certain call 425–227–1221. It is also available
Shahram Daneshmandi, Aerospace Engineer, The Boeing Company Model 737–100, on the Internet at http://
mstockstill on DSK3G9T082PROD with PROPOSALS
International Branch, ANM–116, Transport –200, and –200C series airplanes. This www.regulations.gov by searching for
Airplane Directorate, FAA, 1601 Lind proposed AD is intended to complete and locating Docket No. FAA–2016–
Avenue SW., Renton, WA 98057–3356; certain mandated programs intended to
telephone 425–227–1112; fax 425–227–1149. 7426.
Information may be emailed to: 9-ANM-116- support the airplane reaching its limit of
validity (LOV) of the engineering data Examining the AD Docket
AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate that support the established structural You may examine the AD docket on
principal inspector, or lacking a principal maintenance program. This proposed the Internet at http://
inspector, the manager of the local flight AD would require repetitive detailed, www.regulations.gov by searching for
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ESTIMATED COSTS—Continued
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Repetitive HFEC and fluorescent dye 118 work-hours × $85 per hour = 0 $10,030 per inspection $842,520 per inspection
penetrant inspections. $10,030 per inspection cycle. cycle. cycle.
Replacement ....................................... Up to 252 work-hours × $85 per hour 25,000 Up to $46,420 per in- Up to $3,899,280 per in-
= $21,420 per inspection cycle. spection cycle. spection cycle.
We estimate the following costs to do based on the results of the proposed might need these inspections, repairs,
any necessary inspections, repairs, and inspection. We have no way of and replacements:
replacements that would be required determining the number of aircraft that
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Bolt and Bushing Removal/Inspection, Fabrica- 101 work-hours × $85 per hour = $8,585 ............ $0 $8,585.
tion, and Installation.
Repair and replacement ....................................... Up to 252 work-hours × $85 per hour = $21,420 25,000 Up to $46,420 per inspec-
per inspection cycle. tion cycle.
Authority for This Rulemaking (4) Will not have a significant (d) Subject
Title 49 of the United States Code economic impact, positive or negative, Air Transport Association (ATA) of
specifies the FAA’s authority to issue on a substantial number of small entities America Code 55, Stabilizers.
rules on aviation safety. Subtitle I, under the criteria of the Regulatory (e) Unsafe Condition
section 106, describes the authority of Flexibility Act.
This proposed AD is intended to complete
the FAA Administrator. Subtitle VII: List of Subjects in 14 CFR Part 39 certain mandated programs intended to
Aviation Programs, describes in more support the airplane reaching its limit of
Air transportation, Aircraft, Aviation validity (LOV) of the engineering data that
detail the scope of the Agency’s
safety, Incorporation by reference, support the established structural
authority.
Safety. maintenance program. We are issuing this
We are issuing this rulemaking under
AD to detect and correct cracking in the rear
the authority described in Subtitle VII, The Proposed Amendment spar upper clevis lugs of the center section,
Part A, Subpart III, Section 44701: Accordingly, under the authority and in the rear spar upper lugs of the
‘‘General requirements.’’ Under that delegated to me by the Administrator, horizontal stabilizer which could result in
section, Congress charges the FAA with the FAA proposes to amend 14 CFR part the loss of structural integrity and
promoting safe flight of civil aircraft in controllability of the airplane.
39 as follows:
air commerce by prescribing regulations (f) Compliance
for practices, methods, and procedures PART 39—AIRWORTHINESS Comply with this AD within the
the Administrator finds necessary for DIRECTIVES compliance times specified, unless already
safety in air commerce. This regulation done.
is within the scope of that authority ■ 1. The authority citation for part 39
continues to read as follows: (g) Inspections, Related Investigative and
because it addresses an unsafe condition
Corrective Actions (Service Information
that is likely to exist or develop on Authority: 49 U.S.C. 106(g), 40113, 44701. Tables 1 and 3)
products identified in this rulemaking
§ 39.13 [Amended] At the applicable time specified in table 1
action.
■ 2. The FAA amends § 39.13 by adding or table 3 of paragraph 1.E., ‘‘Compliance,’’
Regulatory Findings of Boeing Alert Service Bulletin 737–
the following new airworthiness 55A1033, Revision 2, dated August 7, 2015,
We determined that this proposed AD directive (AD): except as specified in paragraph (o) of this
would not have federalism implications The Boeing Company: Docket No. FAA– AD: Do detailed, high frequency eddy current
under Executive Order 13132. This 2016–7426; Directorate Identifier 2015– (HFEC), and ultrasonic inspections of the
proposed AD would not have a NM–199–AD. center section rear spar upper clevis lugs for
substantial direct effect on the States, on any cracking, and do all applicable related
(a) Comments Due Date investigative and corrective actions, in
the relationship between the national
We must receive comments by August 26, accordance with the Accomplishment
Government and the States, or on the Instructions of Boeing Alert Service Bulletin
2016.
distribution of power and 737–55A1033, Revision 2, dated August 7,
responsibilities among the various (b) Affected ADs 2015; except as specified in paragraph (p) of
levels of government. This AD affects AD 84–23–05, Amendment this AD. Do all related investigative and
For the reasons discussed above, I 39–4949 (49 FR 45744, November 20, 1984); corrective actions before further flight.
certify this proposed regulation: and AD 86–12–05, Amendment 39–5321 (51 Repeat the inspections thereafter at the
mstockstill on DSK3G9T082PROD with PROPOSALS
(1) Is not a ‘‘significant regulatory FR 18771, May 22, 1986). applicable times specified in table 1 or table
action’’ under Executive Order 12866, 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
(c) Applicability
(2) Is not a ‘‘significant rule’’ under Alert Service Bulletin 737–55A1033,
This AD applies to The Boeing Company Revision 2, dated August 7, 2015.
the DOT Regulatory Policies and Model 737–100, –200, and –200C series
Procedures (44 FR 11034, February 26, airplanes, certificated in any category, as (h) Replacement (Service Information Table
1979), identified in Boeing Alert Service Bulletin 1)
(3) Will not affect intrastate aviation 737–55A1033, Revision 2, dated August 7, For airplanes identified as Group 1,
in Alaska, and 2015. Configuration 1, in Boeing Alert Service
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![Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Proposed Rules 45079
attention of the person identified in To ensure that your comments
DATES: objections to the issues, and subpoena
paragraph (s)(1) of this AD. are considered, we must receive them requests;
(2) Before using any approved AMOC, no later than August 11, 2016. (4) what constitutes the official
notify your appropriate principal inspector, record; and
or lacking a principal inspector, the managerADDRESSES: You may submit comments
by any one of three methods—Internet,
of the local flight standards district office/
(5) the manner in which the Appeals
certificate holding district office. fax, or mail. Do not submit the same Council considers additional evidence.
(3) An AMOC that provides an acceptable comments multiple times or by more Background
level of safety may be used for any repair, than one method. Regardless of which
modification, or alteration required by this method you choose, please state that Over the last few years, we have
AD if it is approved by the Boeing
your comments refer to Docket No. revised many of our regulations to
Commercial Airplanes Organization bolster program integrity and clarify our
Designation Authorization (ODA) that has SSA–2014–0052 so that we may
associate your comments with the policy, procedures, and expectations.
been authorized by the Manager, Los Angeles For example, on June 25, 2014, we made
ACO, to make those findings. To be correct rule.
approved, the repair method, modification Caution: You should be careful to changes to when a claimant must object
deviation, or alteration deviation must meet include in your comments only to appearing at a hearing by video
the certification basis of the airplane and the
information that you wish to make teleconferencing.1 As another example,
approval must specifically refer to this AD. publicly available. We strongly urge you we published a final rule on March 20,
(s) Related Information not to include in your comments any 2015, that clarified a claimant’s duty to
personal information, such as Social inform us about or submit all evidence
(1) For more information about this AD,
that relates to whether or not he or she
contact Payman Soltani, Aerospace Engineer, Security numbers or medical
Airframe Branch, ANM–120L, FAA, Los information. is blind or disabled, subject to two
Angeles ACO, 3960 Paramount Boulevard, 1. Internet: We strongly recommend exceptions for privileged
Lakewood, CA 90712–4137; phone: 562–627– that you submit your comments via the communications.2 We made these and
5313; fax: 562–627–5210; email: Internet. Please visit the Federal other changes specifically to strengthen
Payman.Soltani@faa.gov. the integrity of our programs.
(2) For service information identified in
eRulemaking portal at http://
www.regulations.gov. Use the ‘‘Search’’ As we explained in the final rule on
this AD, contact Boeing Commercial March 20, 2015, ‘‘we believe program
Airplanes, Attention: Data & Services function to find docket number SSA–
Management, P.O. Box 3707, MC 2H–65, 2014–0052. The system will issue a integrity requires us to obtain complete
Seattle, WA 98124–2207; telephone: 206– tracking number to confirm your medical evidence (favorable or
544–5000, extension 1; fax: 206–766–5680; submission. You will not be able to unfavorable) in disability claims.’’ 3
Internet: https://www.myboeingfleet.com. view your comment immediately Although that statement refers to
You may view this referenced service because we must post each comment medical evidence, we reiterate in this
information at the FAA, Transport Airplane proposed rule that a complete
Directorate, 1601 Lind Avenue SW., Renton, manually. It may take up to a week for
your comment to be viewable. evidentiary record is necessary for us to
WA. For information on the availability of make an informed and accurate
this material at the FAA, call 425–227–1221. 2. Fax: Fax comments to (410) 966–
2830. disability determination or decision,
Issued in Renton, Washington, on June 28,
2016. 3. Mail: Mail your comments to the and bolsters program integrity by
Office of Regulations and Reports improving consistency in the
John P. Piccola, Jr.,
Clearance, Social Security adjudication of claims at all levels of the
Acting Manager, Transport Airplane administrative review process. As we
Directorate, Aircraft Certification Service. Administration, 3100 West High Rise
Building, 6401 Security Boulevard, look ahead, we continue to evaluate our
[FR Doc. 2016–16322 Filed 7–11–16; 8:45 am] regulatory and sub-regulatory policies to
Baltimore, Maryland 21235–6401.
BILLING CODE 4910–13–P
Comments are available for public assess where we can make changes to
viewing on the Federal eRulemaking improve accuracy and efficiency in our
portal at http://www.regulations.gov or administrative review processes. To that
SOCIAL SECURITY ADMINISTRATION in person, during regular business end, we are now proposing the changes
hours, by arranging with the contact outlined below.
20 CFR Parts 404, 405 and 416 As we discuss in detail below, we
person identified below.
[Docket No. SSA–2014–0052] FOR FURTHER INFORMATION CONTACT:
have now had time to implement
Maren Weight, Office of Appellate helpful systems changes and review a
RIN 0960–AH71 study performed by the Administrative
Operations, Social Security
Ensuring Program Uniformity at the Administration, 5107 Leesburg Pike, Conference of the United States (ACUS),
Hearing and Appeals Council Levels of Falls Church, VA 22041, (703) 605– in which ACUS evaluated available data
the Administrative Review Process 7100. For information on eligibility or and considered various internal and
filing for benefits, call our national toll- external stakeholder opinions about the
AGENCY: Social Security Administration. impact of our Part 405 rules.4 We are
free number, 1–800–772–1213 or TTY
ACTION: Notice of proposed rulemaking 1–800–325–0778, or visit our Internet 1 79 FR 35926.
(NPRM). site, Social Security Online, at http:// 2 See 80 FR 14828, 20 CFR 404.1512, 416.912.
SUMMARY: We propose to revise our www.socialsecurity.gov. 3 80 FR at 14833.
rules so that more of our procedures at SUPPLEMENTARY INFORMATION: We 4 See Report from Office of the Chairman of the
mstockstill on DSK3G9T082PROD with PROPOSALS
the administrative law judge (ALJ) and Administrative Conference of the United States,
propose revisions to: SSA Disability Benefits Adjudication Process:
Appeals Council levels of our (1) The time-frame for notifying Assessing the Impact of the Region 1 Pilot Program
administrative review process are claimants of a hearing date; (Dec. 23, 2013) (‘‘ACUS Report’’), available at
consistent nationwide. We anticipate (2) the information in our hearing http://acus.gov/sites/default/files/documents/
that these nationally consistent notices; Assessing%20Impact%20of%20Region%20
I%20Pilot%20Program%20Report_12_23_13_
procedures will enable us to administer (3) the period when we require final.pdf. For the specific data reviewed and
our disability programs more efficiently claimants to inform us about or submit opinions collected by ACUS, see Appendix to SSA
and better serve the public. written evidence, written statements, Continued
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Document Created: 2016-07-12 01:59:32
Document Modified: 2016-07-12 01:59:32
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 26, 2016. | |
| Contact | Payman Soltani, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 45075 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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