Airworthiness Directives; The Boeing Company Airplanes, 41894-41897 [2016-14966]

Download as PDF 41894 Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. Airplane Directorate, FAA; or EASA; or Airbus’s EASA Design Organization Approval (DOA). (e) Reason This AD was prompted by a report indicating that during inspections to detect corrosion of the bulk cargo doors, several cracks were discovered. We are issuing this AD to detect and correct cracking of the bulk cargo doors; such cracking could result in rapid airplane decompression or possible loss of the bulk cargo door. (k) Other FAA AD Provisions (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Within 250 flight cycles or 6 months after the effective date of this AD, whichever occurs first, do a general visual inspection of the bulk cargo door frame to identify the existence of any structural repairs, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A53W010–15, Revision 00, including Appendixes 1, 2, and 3, dated December 15, 2015. (h) Detailed Visual Inspection If, during the general visual inspection required in paragraph (g) of this AD, any repair is found on the bulk cargo door frame: Before further flight, do a detailed visual inspection for cracking of the frame at the repaired area, in accordance with the instructions of Airbus AOT A53W010–15, Revision 00, including Appendixes 1, 2, and 3, dated December 15, 2015. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (i) Crack Repair If any cracking is found during the detailed visual inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA Design Organization Approval (DOA). (j) Post-Repair Actions for Crack-Free Frames If no cracking is found during the detailed visual inspection required by paragraph (h) of this AD: Do the actions in paragraphs (j)(1) and (j)(2) of this AD. (1) At the applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD: Send a report of the inspection results to Airbus Service Bulletin Reporting Online Application on Airbus World (https:// w3.airbus.com/). (i) If the inspection was done on or after the effective date of this AD: Submit the report within 60 days after the inspection. (ii) If the inspection was done before the effective date of this AD: Submit the report within 60 days after the effective date of this AD. (2) Within 2,800 flight cycles after the detailed visual inspection required by paragraph (h) of this AD: Do applicable postrepair inspections and repairs, using a method approved by the Manager, International Branch, ANM–116, Transport VerDate Sep<11>2014 16:20 Jun 27, 2016 Jkt 238001 The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0238, dated December 18, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–7269. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. 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. Issued in Renton, Washington, on June 10, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–14968 Filed 6–27–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–7270; Directorate Identifier 2015–NM–116–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737–700 and –700C series airplanes. This proposed AD was prompted by a report that for airplanes with blended winglets, the nose-up pitch trim limit and associated warning for the horizontal stabilizer control system will allow takeoff with incorrect trim settings. This proposed AD would require, depending on airplane configuration, replacing the pitch trim light plates on the flight deck control stand, relocating the position warning horn switches of the horizontal stabilizer, revising the software, removing the placard, and doing related investigative and corrective actions if necessary. We are proposing this AD to prevent take-off with incorrect settings of the horizontal stabilizer pitch trim system. Settings outside of the appropriate pitch trim limits could result in loss of controllability of the airplane during take-off. DATES: We must receive comments on this proposed AD by August 12, 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 Aviation Partners Boeing service information identified in this NPRM, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite 200, Seattle, WA 98168; phone: 206–830–7699; fax: 206–767–3355; email: leng@ aviationpartners.com; Internet: http:// www.aviationpartnersboeing.com. SUMMARY: E:\FR\FM\28JNP1.SGM 28JNP1 Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules For The Boeing Company 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. Boeing Alert Service Bulletin 737–27A1306, dated September 10, 2015, is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7270. 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– 7270; 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: Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6659; fax: 425–917–6590; email: fnu.winarto@faa.gov. SUPPLEMENTARY INFORMATION: asabaliauskas on DSK3SPTVN1PROD with PROPOSALS 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– 2016–7270; Directorate Identifier 2015– NM–116–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy 41895 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. stabilizer trim system, and repairing the light plate switch. We reviewed Aviation Partners Service Bulletin AP737–34–005, dated July 17, 2015. The service information describes procedures for revising the software and removing the placard. 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. Discussion We have received a report that for airplanes with blended winglets, the nose-up pitch trim limit and associated warning for the horizontal stabilizer control system will allow takeoff with incorrect trim settings. The trim control system was recently analyzed for potential nose-up mis-trim occurrences during take-off for airplanes with blended winglets. Results of the analysis indicated that Model 737–700 airplanes with blended winglets are not compliant with the certification rules for specific conditions. This condition, if not corrected, could result in the loss of controllability of the airplane during take-off. FAA’s Determination Related Service Information Under 1 CFR Part 51 We reviewed Aviation Partners Boeing Service Bulletin AP737–27–002, Revision 2, dated March 1, 2016, and Boeing Alert Service Bulletin 737– 27A1306, dated September 10, 2015. The service information describes procedures for replacing the pitch trim light plates on the flight deck control stand, relocating the position warning horn switches of the horizontal stabilizer, revising the software, and doing related investigative and corrective actions. The related investigative actions include verifying that the stabilizer ‘‘B’’ measurement is at a certain dimension, performing a light plate function test, performing a stabilizer functional test, loading and verifying model/engine database software, performing a flight management computer configuration check, and verifying all settings. The corrective actions include adjusting the stabilizer, adjusting the light plate, replacing the light plate, rigging and adjusting the horizontal 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 Boeing Alert Service Bulletin 737–27A1306, dated September 10, 2015, at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7270. Differences Between This Proposed AD and the Service Information The service information specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions 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. Costs of Compliance We estimate that this proposed AD affects 569 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Relocation ...................... Replacement .................. Software installation ....... Up to 4 work-hours × $85 per hour = $340 ........... Up to 3 work-hours × $85 per hour = $255 ........... 2 work-hours × $85 per hour = $170 ..................... VerDate Sep<11>2014 16:20 Jun 27, 2016 Jkt 238001 PO 00000 Frm 00019 Parts cost Fmt 4702 Sfmt 4702 $0 $1,973 0 Cost per product Up to $340 ............. Up to $2,228 .......... 170 ......................... E:\FR\FM\28JNP1.SGM 28JNP1 Cost on U.S. operators Up to $193,460 Up to $1,267,732 96,730 41896 Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules ESTIMATED COSTS—Continued Action Placard Removal (2 airplanes). Labor cost 1 work-hour × $85 per hour = $85 ......................... We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS 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, VerDate Sep<11>2014 Parts cost 16:20 Jun 27, 2016 Jkt 238001 Cost per product 0 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2016–7270; Directorate Identifier 2015– NM–116–AD. (a) Comments Due Date We must receive comments by August 12, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 737–700 and –700C series airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Airplanes having supplemental type certificate ST00830SE installed (Aviation Partners Boeing blended winglets), as identified in Aviation Partners Boeing Service Bulletin AP737–27–002, Revision 2, dated March 1, 2016. (2) Airplanes identified in Boeing Alert Service Bulletin 737–27A1306, dated September 10, 2015. (3) Airplanes identified in Aviation Partners Service Bulletin AP737–34–005, dated July 17, 2015. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Unsafe Condition This AD was prompted by a report that for airplanes with blended winglets, the nose-up pitch trim limit and associated warning for the horizontal stabilizer control system will allow take-off with incorrect trim settings. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 85 ........................... Cost on U.S. operators 170 We are issuing this AD to prevent take-off with incorrect settings of the horizontal stabilizer pitch trim system. Settings outside of the appropriate pitch trim limits could result in loss of controllability of the airplane during take-off. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement, Relocation, and Applicable Related Investigative and Corrective Actions (1) For airplanes identified in paragraph (c)(1) of this AD: Within 72 months after the effective date of this AD, relocate the position warning horn switches of the horizontal stabilizer, replace the pitch trim light plates on the flight deck control stand, revise the software, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP737–27–002, Revision 2, dated March 1, 2016; except as specified in paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. (2) For airplanes identified in paragraph (c)(2) of this AD: Within 72 months after the effective date of this AD, relocate the position warning horn switches of the horizontal stabilizer, replace the pitch trim light plates on the flight deck control stand, revise the software, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1306, dated September 10, 2015, and Aviation Partners Boeing Service Bulletin AP737–27–002, Revision 2, dated March 1, 2016; except as specified in paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. (h) Software Revision and Placard Removal For airplanes identified in paragraph (c)(3) of this AD: Within 72 months after the effective date of this AD, revise the software and remove the placard, in accordance with the Accomplishment Instructions of Aviation Partners Service Bulletin AP737–34–005, dated July 17, 2015. (i) Credit for Actions Accomplished in Accordance With Previous Service Information This paragraph provides credit for the actions specified in paragraphs (g)(1) and (g)(2) of this AD, if those actions were performed before the effective date of this AD using Aviation Partners Boeing Service Bulletin AP737–27–002, dated March 31, 2015; or Aviation Partners Boeing Service Bulletin AP737–27–002, Revision 1, dated August 6, 2015. E:\FR\FM\28JNP1.SGM 28JNP1 Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules (j) Exception to the Service Information Where Aviation Partners Boeing Service Bulletin AP737–27–002, Revision 2, dated March 1, 2016, specifies to contact Boeing for appropriate action, and specifies that action as Required for Compliance (RC): Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 (l)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (j) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6659; fax: 425– 917–6590; email: fnu.winarto@faa.gov. (2) For service information identified in this AD, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite 200, Seattle, WA 98168; phone: 206–830–7699; fax: 206– VerDate Sep<11>2014 16:20 Jun 27, 2016 Jkt 238001 767–3355; email: leng@aviationpartners.com; Internet: http:// www.aviationpartnersboeing.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 14, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–14966 Filed 6–27–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–7267; Directorate Identifier 2016–NM–015–AD] Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–102, –103, and –106 airplanes, Model DHC– 8–200 series airplanes, and Model DHC– 8–300 series airplanes. This proposed AD was prompted by several occurrences of loss of airspeed data on both pilot and co-pilot air speed indicators due to the accumulation of ice on the pitot probes. An investigation revealed that the accumulation of ice was due to inoperative pitot probe heaters. This proposed AD would require replacing the existing circuit breakers in both the left and right side of the pitot heater system with circuit breakers that have higher trip points. We are proposing this AD to prevent circuit breakers from tripping and cutting power supply to the pitot probe heater, which could cause loss of airspeed data and result in the flightcrew not being able to control the airspeed of the airplane. DATES: We must receive comments on this proposed AD by August 12, 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. SUMMARY: Frm 00021 Fmt 4702 • 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 Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone: 416–375–4000; fax: 416–375–4539; email: thd.qseries@ aero.bombardier.com; Internet: http:// www.bombardier.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. Examining the AD Docket RIN 2120–AA64 PO 00000 41897 Sfmt 4702 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7267; 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 Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Assata Dessaline, Aerospace Engineer, Avionics and Services Branch, ANE– 172, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7301; fax: 516–794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–7267; Directorate Identifier 2016–NM–015–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 based on those comments. We will post all comments we receive, without change, to http:// E:\FR\FM\28JNP1.SGM 28JNP1

Agencies

[Federal Register Volume 81, Number 124 (Tuesday, June 28, 2016)]
[Proposed Rules]
[Pages 41894-41897]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14966]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7270; Directorate Identifier 2015-NM-116-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 737-700 and -700C series airplanes. 
This proposed AD was prompted by a report that for airplanes with 
blended winglets, the nose-up pitch trim limit and associated warning 
for the horizontal stabilizer control system will allow take-off with 
incorrect trim settings. This proposed AD would require, depending on 
airplane configuration, replacing the pitch trim light plates on the 
flight deck control stand, relocating the position warning horn 
switches of the horizontal stabilizer, revising the software, removing 
the placard, and doing related investigative and corrective actions if 
necessary. We are proposing this AD to prevent take-off with incorrect 
settings of the horizontal stabilizer pitch trim system. Settings 
outside of the appropriate pitch trim limits could result in loss of 
controllability of the airplane during take-off.

DATES: We must receive comments on this proposed AD by August 12, 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 Aviation Partners Boeing service information identified in this 
NPRM, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite 
200, Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email: 
leng@aviationpartners.com; Internet: http://www.aviationpartnersboeing.com.

[[Page 41895]]

    For The Boeing Company 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. Boeing Alert Service Bulletin 737-27A1306, dated September 
10, 2015, is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7270.

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-
7270; 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: Fnu Winarto, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6659; fax: 425-917-6590; email: 
fnu.winarto@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-7270; 
Directorate Identifier 2015-NM-116-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received a report that for airplanes with blended winglets, 
the nose-up pitch trim limit and associated warning for the horizontal 
stabilizer control system will allow takeoff with incorrect trim 
settings. The trim control system was recently analyzed for potential 
nose-up mis-trim occurrences during take-off for airplanes with blended 
winglets. Results of the analysis indicated that Model 737-700 
airplanes with blended winglets are not compliant with the 
certification rules for specific conditions. This condition, if not 
corrected, could result in the loss of controllability of the airplane 
during take-off.

Related Service Information Under 1 CFR Part 51

    We reviewed Aviation Partners Boeing Service Bulletin AP737-27-002, 
Revision 2, dated March 1, 2016, and Boeing Alert Service Bulletin 737-
27A1306, dated September 10, 2015. The service information describes 
procedures for replacing the pitch trim light plates on the flight deck 
control stand, relocating the position warning horn switches of the 
horizontal stabilizer, revising the software, and doing related 
investigative and corrective actions.
    The related investigative actions include verifying that the 
stabilizer ``B'' measurement is at a certain dimension, performing a 
light plate function test, performing a stabilizer functional test, 
loading and verifying model/engine database software, performing a 
flight management computer configuration check, and verifying all 
settings.
    The corrective actions include adjusting the stabilizer, adjusting 
the light plate, replacing the light plate, rigging and adjusting the 
horizontal stabilizer trim system, and repairing the light plate 
switch.
    We reviewed Aviation Partners Service Bulletin AP737-34-005, dated 
July 17, 2015. The service information describes procedures for 
revising the software and removing the placard.
    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 Boeing Alert Service Bulletin 737-27A1306, dated September 10, 
2015, at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-7270.

Differences Between This Proposed AD and the Service Information

    The service information specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions 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.

Costs of Compliance

    We estimate that this proposed AD affects 569 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Relocation.....................  Up to 4 work-hours x                 $0  Up to $340........  Up to $193,460
                                  $85 per hour = $340.
Replacement....................  Up to 3 work-hours x             $1,973  Up to $2,228......  Up to $1,267,732
                                  $85 per hour = $255.
Software installation..........  2 work-hours x $85 per                0  170...............  96,730
                                  hour = $170.

[[Page 41896]]

 
Placard Removal (2 airplanes)..  1 work-hour x $85 per                 0  85................  170
                                  hour = $85.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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-2016-7270; Directorate Identifier 
2015-NM-116-AD.

(a) Comments Due Date

    We must receive comments by August 12, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-700 and -700C 
series airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) 
of this AD, certificated in any category.
    (1) Airplanes having supplemental type certificate ST00830SE 
installed (Aviation Partners Boeing blended winglets), as identified 
in Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 
2, dated March 1, 2016.
    (2) Airplanes identified in Boeing Alert Service Bulletin 737-
27A1306, dated September 10, 2015.
    (3) Airplanes identified in Aviation Partners Service Bulletin 
AP737-34-005, dated July 17, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Unsafe Condition

    This AD was prompted by a report that for airplanes with blended 
winglets, the nose-up pitch trim limit and associated warning for 
the horizontal stabilizer control system will allow take-off with 
incorrect trim settings. We are issuing this AD to prevent take-off 
with incorrect settings of the horizontal stabilizer pitch trim 
system. Settings outside of the appropriate pitch trim limits could 
result in loss of controllability of the airplane during take-off.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Replacement, Relocation, and Applicable Related Investigative and 
Corrective Actions

    (1) For airplanes identified in paragraph (c)(1) of this AD: 
Within 72 months after the effective date of this AD, relocate the 
position warning horn switches of the horizontal stabilizer, replace 
the pitch trim light plates on the flight deck control stand, revise 
the software, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Aviation Partners Boeing Service Bulletin AP737-27-
002, Revision 2, dated March 1, 2016; except as specified in 
paragraph (j) of this AD. Do all applicable related investigative 
and corrective actions before further flight.
    (2) For airplanes identified in paragraph (c)(2) of this AD: 
Within 72 months after the effective date of this AD, relocate the 
position warning horn switches of the horizontal stabilizer, replace 
the pitch trim light plates on the flight deck control stand, revise 
the software, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-27A1306, dated 
September 10, 2015, and Aviation Partners Boeing Service Bulletin 
AP737-27-002, Revision 2, dated March 1, 2016; except as specified 
in paragraph (j) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

(h) Software Revision and Placard Removal

    For airplanes identified in paragraph (c)(3) of this AD: Within 
72 months after the effective date of this AD, revise the software 
and remove the placard, in accordance with the Accomplishment 
Instructions of Aviation Partners Service Bulletin AP737-34-005, 
dated July 17, 2015.

(i) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This paragraph provides credit for the actions specified in 
paragraphs (g)(1) and (g)(2) of this AD, if those actions were 
performed before the effective date of this AD using Aviation 
Partners Boeing Service Bulletin AP737-27-002, dated March 31, 2015; 
or Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 
1, dated August 6, 2015.

[[Page 41897]]

(j) Exception to the Service Information

    Where Aviation Partners Boeing Service Bulletin AP737-27-002, 
Revision 2, dated March 1, 2016, specifies to contact Boeing for 
appropriate action, and specifies that action as Required for 
Compliance (RC): Before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(k) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 (l)(1) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. For a repair method to 
be approved, the repair, modification deviation, or alteration 
deviation must meet the certification basis of the airplane, and the 
approval must specifically refer to this AD.
    (4) Except as required by paragraph (j) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(l) Related Information

    (1) For more information about this AD, contact Fnu Winarto, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6659; fax: 425-917-6590; 
email: fnu.winarto@faa.gov.
    (2) For service information identified in this AD, contact 
Aviation Partners Boeing, 2811 South 102nd Street, Suite 200, 
Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email: 
leng@aviationpartners.com; Internet: http://www.aviationpartnersboeing.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 14, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-14966 Filed 6-27-16; 8:45 am]
 BILLING CODE 4910-13-P