Airworthiness Directives; BAE Systems (Operations) Limited, 72557-72561 [2016-24201]

Download as PDF Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Proposed Rules the Accomplishment Instructions of ASB 737–53A1267 R1, as applicable. (2) Do a one-time detailed inspection for any defect of the production countersunk rivet heads on both forward and aft fastener columns, left and right sides, at STA 259.5 circumferential butt splice, in accordance with Part 3 of the Accomplishment Instructions of ASB 737–53A1267 R1. (i) Optional Terminating Repairs (1) For airplanes identified as Group 1, Configuration 1 in ASB 737–53A1267 R1: Doing the skin trim-out repair specified in Part 5 of the Accomplishment Instructions of ASB 737–53A1267 R1 terminates the repetitive inspections required by paragraph (h) of this AD that are specified in Part 1 of the Accomplishment Instructions of ASB 737–53A1267 R1 only; all other repetitive inspections required by paragraph (h) of this AD must be done, except as provided by paragraph (i)(2) of this AD. (2) For airplanes identified as Group 1, Configuration 1 in ASB 737–53A1267 R1: Doing the skin repair specified in Part 4 of the Accomplishment Instructions of ASB 737–53A1267 R1, terminates the repetitive inspections required by paragraph (h) of this AD that are specified in Part 1 and Part 2 of the Accomplishment Instructions of ASB 737–53A1267 R1 for the repaired area only; all other repetitive inspections required by paragraph (h) of this AD must be done, except as provided by paragraph (i)(1) of this AD. mstockstill on DSK3G9T082PROD with PROPOSALS (j) Exceptions to Service Information (1) Where paragraph 1.E., ‘‘Compliance,’’ of ASB 737–53A1267 R1, specifies a compliance time ‘‘after the Revision 1 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although ASB 737–53A1267 R1, specifies to contact Boeing for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight 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, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-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 VerDate Sep<11>2014 16:24 Oct 19, 2016 Jkt 241001 Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) AMOCs approved previously for AD 2007–26–04 are approved as AMOCs for the corresponding provisions of this AD. (5) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (k)(5)(i) and (k)(5)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or sub-step is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or sub-step. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6430; fax: 425–917–6590; email: wade.sullivan@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–66–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on September 30, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–24262 Filed 10–19–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 72557 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9186; Directorate Identifier 2015–NM–160–AD] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2012–16– 08, for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ series airplanes. AD 2012–16–08 currently requires repetitive detailed inspections for bulging, surface anomalies, and cracking of the fuselage skin adjacent to the discharge valves, and repair and application of additional sealant in the affected area if necessary. Since we issued AD 2012–16–08, it was found that airplanes on which a certain modification was incorporated during production were excluded from the applicability, but are also affected by the condition that precipitated AD 2012– 16–08. This proposed AD would retain the requirements of AD 2012–16–08, expand the applicability, and require an additional one-time inspection for the presence of water traps/air driers to determine which airplanes must be inspected. We are proposing this AD to detect and correct bulging, surface anomalies, and cracking that could propagate towards the forward discharge valve outlet and result in the failure of the fuselage skin, leading to a possible sudden loss of cabin pressure and injury to occupants. DATES: We must receive comments on this proposed AD by December 5, 2016. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: E:\FR\FM\20OCP1.SGM 20OCP1 72558 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Proposed Rules For service information identified in this NPRM, contact BAE Systems (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@ baesystems.com; Internet http:// www.baesystems.com/Businesses/ RegionalAircraft/index.htm. 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 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9186; 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: Theodore Thompson, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227– 1175; fax 425–227–1149. SUPPLEMENTARY INFORMATION: mstockstill on DSK3G9T082PROD with PROPOSALS 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–2016–9186; Directorate Identifier 2015–NM–160–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:// 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. VerDate Sep<11>2014 16:24 Oct 19, 2016 Jkt 241001 Discussion On July 31, 2012, we issued AD 2012– 16–08, Amendment 39–17155 (77 FR 48420, August 14, 2012) (‘‘AD 2012–16– 08’’). AD 2012–16–08 requires repetitive detailed inspections for bulging, surface anomalies, and cracking of the fuselage skin adjacent to the discharge valves, and repair and application of additional sealant in the affected area if necessary. Since we issued AD 2012–16–08, it was found that airplanes that have incorporated auto-pressurization modification No. HCM50259A during production, which were excluded from the applicability, are also affected by this condition. In addition, and in order to simplify instructions and determine affected airplanes, BAE Systems (Operations) Limited issued BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21–162, Revision 4, dated January 28, 2015, introducing a one-time inspection to determine if water trap/air driers are installed. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0180, dated August 28, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146–RJ series airplanes. The MCAI states: An operator reported finding cracking and surface anomalies (bulges and/or dents) of the fuselage skin at the water trap/air drier unit of the forward discharge valve, located between fuselage frame (FR) 22 and FR23 and between stringers 22 and 23. Further investigation established that these surface anomalies were due to corrosion beneath the water trap/air drier unit that has resulted in cracking of the fuselage skin This condition, if not detected and corrected, could lead to failure of the fuselage skin, possibly resulting in loss of cabin pressure and injury to occupants. To address this potential unsafe condition, EASA issued AD 2011–0099 [which corresponds to FAA AD 2012–16–08] to require repetitive detailed visual inspections (DVI) of the fuselage skin adjacent to the front and rear discharge valves to check for bulging, surface anomalies and cracking, and, depending on findings, accomplishment of applicable corrective action(s), and the application of additional sealant in the affected area. Since that [EASA] AD was issued, it was found that aeroplanes that have incorporated auto-pressurisation modification No. HCM50259A during production, which were excluded from the Applicability, were also affected by this condition. In addition, and in order to simplify instructions for applicability, BAE Systems PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 (Operations) Limited issued Revision 4 of Inspection Service Bulletin (ISB) No. 21–162, introducing a one-time inspection to identify if water trap/air driers are installed. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2011–0099, which is superseded, expands the Applicability and requires the additional one-time inspection as specified in the latest ISB revision. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9186. Related Service Information Under 1 CFR Part 51 BAE Systems (Operations) Limited has issued BAE Systems (Operations) Limited Service Bulletin ISB.21–162, Revision 4, dated January 28, 2015. The service information describes procedures for a visual inspection of the internal fuselage at the location of the water trap/air driers to determine if water trap/air driers are installed; an external DVI for bulging, surface anomalies, and cracking of the fuselage skin adjacent to the forward and rear discharge valve outlets; repair; and sealant application. BAE Systems (Operations) Limited has also issued the following service information, which describes procedures for structural repairs. • Subject 53–00–00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAE SYSTEMS BAe 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 100–200, Revision 68, dated October 15, 2014. • Subject 53–00–00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAe SYSTEMS BAE 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 300, Revision 46, dated October 15, 2014. 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 and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or E:\FR\FM\20OCP1.SGM 20OCP1 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Proposed Rules develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 4 airplanes of U.S. registry. The actions required by AD 2012–16– 08 and retained in this proposed AD take about 8 work-hours per product, at an average labor rate of $85 per workhour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2012–16–08 is $680 per product. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $2,720, or $680 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking mstockstill on DSK3G9T082PROD with PROPOSALS 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; 16:24 Oct 19, 2016 Jkt 241001 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 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. VerDate Sep<11>2014 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. [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2012–16–08, Amendment 39–17155 (77 FR 48420, August 14, 2012), and adding the following new AD: ■ BAE Systems (Operations) Limited: Docket No. FAA–2016–9186; Directorate Identifier 2015–NM–160–AD. (a) Comments Due Date We must receive comments by December 5, 2016. (b) Affected ADs This AD replaces AD 2012–16–08, Amendment 39–17155 (77 FR 48420, August 14, 2012) (‘‘AD 2012–16–08’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all serial numbers. (1) BAE Systems (Operations) Limited Model BAe 146–100A, –200A, and –300A airplanes. (2) BAE Systems (Operations) Limited Model Avro 146–RJ70A, 146–RJ85A, and 146–RJ100A airplanes. (d) Subject Air Transport Association (ATA) of America Code 21, Air Conditioning. (e) Reason This AD was prompted by reports of cracking and surface anomalies of the fuselage skin at the water trap/air drier unit of the forward discharge valve due to corrosion, and the determination that airplanes on which auto-pressurization modification No. HCM50259A was incorporated during production were PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 72559 excluded from the applicability of AD 2012– 16–08, but are also affected by this condition. We are issuing this AD to detect and correct bulging, surface anomalies, and cracking that could propagate towards the forward discharge valve outlet and result in the failure of the fuselage skin, leading to a possible sudden loss of cabin pressure and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Detailed Inspection of External Fuselage Skin, With Specific Delegation Approval Language This paragraph restates the requirements of paragraph (g) of AD 2012–16–08, with specific delegation approval language. For all airplanes except airplanes that have incorporated auto-pressurization modification HCM50259A during production: Within 12 months after September 18, 2012 (the effective date of AD 2012–16–08), do a detailed inspection to check for bulging, surface anomalies, and cracking of the fuselage skin adjacent to the discharge valve outlets (one frame fore and aft, one stringer above and below), in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21– 162, Revision 1, dated September 16, 2010. Repeat the inspection thereafter at intervals not to exceed 24 months. (1) If any bulging, surface anomalies, or cracking of the fuselage skin is found to be within the criteria defined in Subject 53–00– 00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAE SYSTEMS BAe 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 100–200, Revision 66, dated October 15, 2011 (for Model 146–100A and –200A, and Avro 146–RJ70A and 146–RJ85A airplanes); or Subject 53–00–00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAe SYSTEMS BAE 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 300, Revision 44, dated October 15, 2011 (for Model 146–300A and Avro 146– RJ100A airplanes): Before further flight, repair the damage, in accordance with the Accomplishment Instructions specified in BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21–162, Revision 1, dated September 16, 2010. (2) If any bulging, surface anomalies, or cracking of the fuselage skin is found exceeding the criteria specified by Subject 53–00–00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAE SYSTEMS BAe 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 100–200, Revision 66, dated October 15, 2011 (for Model 146–100A and –200A, and Avro 146–RJ70A and 146–RJ85A airplanes); or Subject 53–00–00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAE SYSTEMS BAE 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 300, Revision 44, dated October 15, 2011 (for Model 146–300A and Avro 146– RJ100A airplanes): Before further flight, E:\FR\FM\20OCP1.SGM 20OCP1 72560 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Proposed Rules repair the condition according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited’s EASA Design Organization Approval (DOA). (h) Retained Application of Sealant, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2012–16–08, with no changes. For all airplanes except airplanes on which auto-pressurization modification HCM50259A was incorporated during production: Within 24 months after September 18, 2012 (the effective date of AD 2012–16–08), unless a repair has already been accomplished in accordance with paragraph (g) of this AD, apply additional PR1422A–2 or PR1764B–2 edge sealant between the water trap/air drier and the fuselage skin, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21–162, Revision 1, dated September 16, 2010. Application of additional sealant does not constitute terminating action for the repetitive detailed inspections required by paragraph (g) of this AD. Accomplishment of a repair as required by paragraph (g) of this AD terminates the repetitive inspection requirements of paragraph (g) of this AD. mstockstill on DSK3G9T082PROD with PROPOSALS (i) New Requirement of This AD: Inspection for Water Traps/Air Driers Within 12 months after the effective date of this AD, inspect the airplane to determine whether water traps/air driers are installed, in accordance with paragraph 2.C of BAE Systems (Operations) Limited Service Bulletin ISB.21–162, Revision 4, dated January 28, 2015 (‘‘ISB.21–162 R4’’). If there are no water traps/air driers installed on an airplane, then no further inspections are required by this AD, except as required by paragraph (n) of this AD. (j) New Requirement of This AD: Repetitive Inspections For airplanes that have water traps/air driers installed, determined as required by paragraph (i) of this AD: Within 12 months after the effective date of this AD, accomplish a detailed visual inspection for bulging, surface anomalies, and cracking of the external fuselage skin adjacent to the discharge valve outlets (one frame bay fore and aft, one stringer above and below), in accordance with the Accomplishment Instructions of paragraph 2.C. of ISB.21–162 R4. Repeat the inspection of the external fuselage skin adjacent to the discharge valve outlets thereafter at intervals not to exceed 24 months. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (k) New Requirement of This AD: Corrective Actions If, during any detailed visual inspection required by paragraph (j) of this AD, any bulging, surface anomalies, or cracking is found, before further flight, accomplish the VerDate Sep<11>2014 16:24 Oct 19, 2016 Jkt 241001 applicable corrective action as specified in paragraphs (k)(1) and (k)(2) this AD. (1) If any bulging, surface anomalies, or cracking is found to be within the criteria as specified in the applicable service information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of paragraph 2.G. of ISB.21–162 R4. (i) For Model BAe 146–100A and –200A airplanes, and Model Avro 146–RJ70A and 146–RJ85A airplanes: Subject 53–00–00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAE SYSTEMS BAe 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 100–200, Revision 68, dated October 15, 2014. (ii) For Model BAe 146–300A airplanes and Model Avro 146–RJ100A airplanes: Subject 53–00–00, ‘‘Fuselage, General Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAe SYSTEMS BAE 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 300, Revision 46, dated October 15, 2014. (2) If any bulging, surface anomalies, or cracking is found exceeding the criteria as specified in the applicable service information specified in paragraph (k)(1)(i) or (k)(1)(ii) 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 BAE Systems (Operations) Limited’s EASA DOA. (l) New Requirement of This AD: Application of Sealant Within 24 months after the effective date of this AD, unless a repair has already been accomplished as required by paragraph (k) of this AD, apply additional sealant, in accordance with the Accomplishment Instructions of paragraph 2.C.(3) of ISB.21– 162 R4. Application of additional sealant on an airplane does not constitute terminating action for the repetitive inspections required by paragraph (j) of this AD for that airplane. (m) New Terminating Action for Inspections Required by Paragraph (j) of This AD Accomplishment of a repair on the forward (FWD) or aft (AFT) position as required by paragraph (k) of this AD constitutes terminating action for the repetitive inspections required by paragraph (j) of this AD for that FWD or AFT position. (n) New Requirement of This AD: Actions for Airplanes on Which Water Trap/Air Driers Are Installed After the Effective Date of This AD For airplanes that, determined as required by paragraph (i) of this AD, do not have water traps/air driers installed: If water traps/air driers are installed in service after the effective date of this AD, accomplish the actions required by paragraphs (j), (k), and (l) of this AD on that airplane within the applicable compliance times specified in paragraphs (j), (k), and (l) of this AD; except that where paragraphs (j) and (l) of this AD refer to ‘‘the effective date of this AD,’’ this AD requires compliance within the specified compliance time after the installation of water traps/air driers. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 (o) Credit for Previous Actions (1) This paragraph provides credit for inspections and sealant applications required by paragraphs (g) and (h) of this AD, if those actions were performed before September 18, 2012 (the effective date of AD 2012–16–08), using BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.21– 162, dated June 7, 2010. (2) This paragraph provides credit for using criteria defined in the following subject of the applicable structural repair manual, as required by paragraphs (g)(1) and (g)(2) of this AD, if those criteria were used before September 18, 2012 (the effective date of AD 2012–16–08), using Subject 53–00–00, ‘‘Fuselage, General—Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAE SYSTEMS BAe 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 100–200, Revision 65, dated September 15, 2010 (for Model 146–100A and –200A, and Avro 146–RJ70A and 146–RJ85A airplanes); or Subject 53–00– 00, ‘‘Fuselage, General—Description,’’ of Chapter 53, ‘‘Fuselage,’’ of the BAE SYSTEMS BAe 146 Series/AVRO 146–RJ Series Structural Repair Manual for Series 300, Revision 43, dated September 15, 2010 (for Model 146–300A and Avro 146–RJ100A airplanes). (3) This paragraph provides credit for actions required by paragraphs (i), (j), and (l) of this AD, if those actions were performed before the effective date of this AD using any of the service information specified in paragraphs (i)(3)(i) through (i)(3)(iv) of this AD. (i) BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21–162, dated June 7, 2010. (ii) BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21–162, Revision 1, dated September 16, 2010. (iii) BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21–162, Revision 2, dated December 12, 2012. (iv) BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21–162, Revision 3, dated January 15, 2013. (p) Other FAA AD Provisions 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: Theodore Thompson, Aerospace Engineer, telephone 425–227–1175; 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: As of the effective date of this AD, for any requirement E:\FR\FM\20OCP1.SGM 20OCP1 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Proposed Rules 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 European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0180, dated August 28, 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–2016–9186. (2) For service information identified in this AD, contact BAE Systems (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@ baesystems.com; Internet http:// www.baesystems.com/Businesses/ RegionalAircraft/index.htm. 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 September 28, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–24201 Filed 10–19–16; 8:45 am] mstockstill on DSK3G9T082PROD with PROPOSALS BILLING CODE 4910–13–P VerDate Sep<11>2014 16:24 Oct 19, 2016 Jkt 241001 DEPARTMENT OF THE TREASURY Internal Revenue Service [REG–103380–05] RIN 1545–BE31 Excise Tax; Tractors, Trailers, Trucks, and Tires; Definition of Highway Vehicle; Hearing Internal Revenue Service (IRS), Treasury. ACTION: Notice of a public hearing on notice of proposed rulemaking. AGENCY: This document provides a notice of public hearing on proposed regulations relating to the excise taxes imposed on the sale of highway tractors, trailers, trucks, and tires; the use of heavy vehicles on the highway; and the definition of highway vehicle related to these and other taxes. DATES: The public hearing is being held on Monday, November 21, 2016, at 10:00 a.m. The IRS must receive outlines of the topics to be discussed at the public hearing by Monday, November 7, 2016. ADDRESSES: The public hearing is being held in the IRS Auditorium, Internal Revenue Service Building, 1111 Constitution Avenue NW., Washington, DC 20224. Due to building security procedures, visitors must enter at the Constitution Avenue entrance. In addition, all visitors must present photo identification to enter the building. Send Submissions to CC:PA:LPD:PR (REG–103380–05), Room 5205, Internal Revenue Service, P.O. Box 7604, Ben Franklin Station, Washington, DC 20044. Submissions may be handdelivered Monday through Friday to CC:PA:LPD:PR (REG–103380–05), Couriers Desk, Internal Revenue Service, 1111 Constitution Avenue NW., Washington, DC 20224 or sent electronically via the Federal eRulemaking Portal at PO 00000 Frm 00011 Fmt 4702 Sfmt 9990 www.regulations.gov (IRS REG–103380– 05). FOR FURTHER INFORMATION CONTACT: 26 CFR Parts 41, 48, and 145 SUMMARY: 72561 Concerning the proposed regulations, Celia Gabrysh (202) 317–6855; concerning submissions of comments, the hearing and/or to be placed on the building access list to attend the hearing Regina Johnson at (202) 317–6901 (not toll-free numbers). The subject of the public hearing is the notice of proposed rulemaking (REG– 103380–05) that was published in the Federal Register on Thursday, March 31, 2016 (81 FR 18544). The rules of 26 CFR 601.601(a)(3) apply to the hearing. Persons who wish to present oral comments at the hearing that submitted written comments by June 29, 2016, must submit an outline of the topics to be addressed and the amount of time to be devoted to each topic by Monday, November 7, 2016. A period of 10 minutes is allotted to each person for presenting oral comments. After the deadline for receiving outlines has passed, the IRS will prepare an agenda containing the schedule of speakers. Copies of the agenda will be made available, free of charge, at the hearing or by contacting the Publications and Regulations Branch at (202) 317–6901 (not a toll-free number). Because of access restrictions, the IRS will not admit visitors beyond the immediate entrance area more than 30 minutes before the hearing starts. For information about having your name placed on the building access list to attend the hearing, see the FOR FURTHER INFORMATION CONTACT section of this document. SUPPLEMENTARY INFORMATION: Martin V. Franks, Chief, Publications and Regulations Branch, Legal Processing Division, Associate Chief Counsel (Procedure and Administration). [FR Doc. 2016–25376 Filed 10–19–16; 8:45 am] BILLING CODE 4830–01–P E:\FR\FM\20OCP1.SGM 20OCP1

Agencies

[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)]
[Proposed Rules]
[Pages 72557-72561]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24201]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9186; Directorate Identifier 2015-NM-160-AD]
RIN 2120-AA64


Airworthiness Directives; BAE Systems (Operations) Limited

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-16-
08, for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 
146-RJ series airplanes. AD 2012-16-08 currently requires repetitive 
detailed inspections for bulging, surface anomalies, and cracking of 
the fuselage skin adjacent to the discharge valves, and repair and 
application of additional sealant in the affected area if necessary. 
Since we issued AD 2012-16-08, it was found that airplanes on which a 
certain modification was incorporated during production were excluded 
from the applicability, but are also affected by the condition that 
precipitated AD 2012-16-08. This proposed AD would retain the 
requirements of AD 2012-16-08, expand the applicability, and require an 
additional one-time inspection for the presence of water traps/air 
driers to determine which airplanes must be inspected. We are proposing 
this AD to detect and correct bulging, surface anomalies, and cracking 
that could propagate towards the forward discharge valve outlet and 
result in the failure of the fuselage skin, leading to a possible 
sudden loss of cabin pressure and injury to occupants.

DATES: We must receive comments on this proposed AD by December 5, 
2016.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

[[Page 72558]]

    For service information identified in this NPRM, contact BAE 
Systems (Operations) Limited, Customer Information Department, 
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United 
Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email 
RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/RegionalAircraft/index.htm. 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

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9186; 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: Theodore Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1175; 
fax 425-227-1149.

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-2016-9186; 
Directorate Identifier 2015-NM-160-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://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

    On July 31, 2012, we issued AD 2012-16-08, Amendment 39-17155 (77 
FR 48420, August 14, 2012) (``AD 2012-16-08''). AD 2012-16-08 requires 
repetitive detailed inspections for bulging, surface anomalies, and 
cracking of the fuselage skin adjacent to the discharge valves, and 
repair and application of additional sealant in the affected area if 
necessary.
    Since we issued AD 2012-16-08, it was found that airplanes that 
have incorporated auto-pressurization modification No. HCM50259A during 
production, which were excluded from the applicability, are also 
affected by this condition. In addition, and in order to simplify 
instructions and determine affected airplanes, BAE Systems (Operations) 
Limited issued BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 4, dated January 28, 2015, introducing a 
one-time inspection to determine if water trap/air driers are 
installed.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0180, dated August 28, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all BAE Systems 
(Operations) Limited Model BAe 146 series airplanes and Model Avro 146-
RJ series airplanes. The MCAI states:

    An operator reported finding cracking and surface anomalies 
(bulges and/or dents) of the fuselage skin at the water trap/air 
drier unit of the forward discharge valve, located between fuselage 
frame (FR) 22 and FR23 and between stringers 22 and 23. Further 
investigation established that these surface anomalies were due to 
corrosion beneath the water trap/air drier unit that has resulted in 
cracking of the fuselage skin
    This condition, if not detected and corrected, could lead to 
failure of the fuselage skin, possibly resulting in loss of cabin 
pressure and injury to occupants.
    To address this potential unsafe condition, EASA issued AD 2011-
0099 [which corresponds to FAA AD 2012-16-08] to require repetitive 
detailed visual inspections (DVI) of the fuselage skin adjacent to 
the front and rear discharge valves to check for bulging, surface 
anomalies and cracking, and, depending on findings, accomplishment 
of applicable corrective action(s), and the application of 
additional sealant in the affected area.
    Since that [EASA] AD was issued, it was found that aeroplanes 
that have incorporated auto-pressurisation modification No. 
HCM50259A during production, which were excluded from the 
Applicability, were also affected by this condition.
    In addition, and in order to simplify instructions for 
applicability, BAE Systems (Operations) Limited issued Revision 4 of 
Inspection Service Bulletin (ISB) No. 21-162, introducing a one-time 
inspection to identify if water trap/air driers are installed.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0099, which is superseded, expands the 
Applicability and requires the additional one-time inspection as 
specified in the latest ISB revision.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9186.

Related Service Information Under 1 CFR Part 51

    BAE Systems (Operations) Limited has issued BAE Systems 
(Operations) Limited Service Bulletin ISB.21-162, Revision 4, dated 
January 28, 2015. The service information describes procedures for a 
visual inspection of the internal fuselage at the location of the water 
trap/air driers to determine if water trap/air driers are installed; an 
external DVI for bulging, surface anomalies, and cracking of the 
fuselage skin adjacent to the forward and rear discharge valve outlets; 
repair; and sealant application.
    BAE Systems (Operations) Limited has also issued the following 
service information, which describes procedures for structural repairs.
     Subject 53-00-00, ``Fuselage, General Description,'' of 
Chapter 53, ``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ 
Series Structural Repair Manual for Series 100-200, Revision 68, dated 
October 15, 2014.
     Subject 53-00-00, ``Fuselage, General Description,'' of 
Chapter 53, ``Fuselage,'' of the BAe SYSTEMS BAE 146 Series/AVRO 146-RJ 
Series Structural Repair Manual for Series 300, Revision 46, dated 
October 15, 2014.
    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 and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or

[[Page 72559]]

develop on other products of these same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 4 airplanes of U.S. 
registry.
    The actions required by AD 2012-16-08 and retained in this proposed 
AD take about 8 work-hours per product, at an average labor rate of $85 
per work-hour. Required parts cost about $0 per product. Based on these 
figures, the estimated cost of the actions that are required by AD 
2012-16-08 is $680 per product.
    We also estimate that it would take about 8 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $2,720, or $680 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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 removing Airworthiness Directive (AD) 
2012-16-08, Amendment 39-17155 (77 FR 48420, August 14, 2012), and 
adding the following new AD:

BAE Systems (Operations) Limited: Docket No. FAA-2016-9186; 
Directorate Identifier 2015-NM-160-AD.

(a) Comments Due Date

    We must receive comments by December 5, 2016.

(b) Affected ADs

    This AD replaces AD 2012-16-08, Amendment 39-17155 (77 FR 48420, 
August 14, 2012) (``AD 2012-16-08'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all serial 
numbers.
    (1) BAE Systems (Operations) Limited Model BAe 146-100A, -200A, 
and -300A airplanes.
    (2) BAE Systems (Operations) Limited Model Avro 146-RJ70A, 146-
RJ85A, and 146-RJ100A airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 21, Air 
Conditioning.

(e) Reason

    This AD was prompted by reports of cracking and surface 
anomalies of the fuselage skin at the water trap/air drier unit of 
the forward discharge valve due to corrosion, and the determination 
that airplanes on which auto-pressurization modification No. 
HCM50259A was incorporated during production were excluded from the 
applicability of AD 2012-16-08, but are also affected by this 
condition. We are issuing this AD to detect and correct bulging, 
surface anomalies, and cracking that could propagate towards the 
forward discharge valve outlet and result in the failure of the 
fuselage skin, leading to a possible sudden loss of cabin pressure 
and injury to occupants.

(f) Compliance

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

(g) Retained Detailed Inspection of External Fuselage Skin, With 
Specific Delegation Approval Language

    This paragraph restates the requirements of paragraph (g) of AD 
2012-16-08, with specific delegation approval language. For all 
airplanes except airplanes that have incorporated auto-
pressurization modification HCM50259A during production: Within 12 
months after September 18, 2012 (the effective date of AD 2012-16-
08), do a detailed inspection to check for bulging, surface 
anomalies, and cracking of the fuselage skin adjacent to the 
discharge valve outlets (one frame fore and aft, one stringer above 
and below), in accordance with the Accomplishment Instructions of 
BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21-
162, Revision 1, dated September 16, 2010. Repeat the inspection 
thereafter at intervals not to exceed 24 months.
    (1) If any bulging, surface anomalies, or cracking of the 
fuselage skin is found to be within the criteria defined in Subject 
53-00-00, ``Fuselage, General Description,'' of Chapter 53, 
``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series 
Structural Repair Manual for Series 100-200, Revision 66, dated 
October 15, 2011 (for Model 146-100A and -200A, and Avro 146-RJ70A 
and 146-RJ85A airplanes); or Subject 53-00-00, ``Fuselage, General 
Description,'' of Chapter 53, ``Fuselage,'' of the BAe SYSTEMS BAE 
146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 
300, Revision 44, dated October 15, 2011 (for Model 146-300A and 
Avro 146-RJ100A airplanes): Before further flight, repair the 
damage, in accordance with the Accomplishment Instructions specified 
in BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.21-162, Revision 1, dated September 16, 2010.
    (2) If any bulging, surface anomalies, or cracking of the 
fuselage skin is found exceeding the criteria specified by Subject 
53-00-00, ``Fuselage, General Description,'' of Chapter 53, 
``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series 
Structural Repair Manual for Series 100-200, Revision 66, dated 
October 15, 2011 (for Model 146-100A and -200A, and Avro 146-RJ70A 
and 146-RJ85A airplanes); or Subject 53-00-00, ``Fuselage, General 
Description,'' of Chapter 53, ``Fuselage,'' of the BAE SYSTEMS BAE 
146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 
300, Revision 44, dated October 15, 2011 (for Model 146-300A and 
Avro 146-RJ100A airplanes): Before further flight,

[[Page 72560]]

repair the condition according to a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or BAE Systems 
(Operations) Limited's EASA Design Organization Approval (DOA).

(h) Retained Application of Sealant, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-16-08, with no changes. For all airplanes except airplanes on 
which auto-pressurization modification HCM50259A was incorporated 
during production: Within 24 months after September 18, 2012 (the 
effective date of AD 2012-16-08), unless a repair has already been 
accomplished in accordance with paragraph (g) of this AD, apply 
additional PR1422A-2 or PR1764B-2 edge sealant between the water 
trap/air drier and the fuselage skin, in accordance with the 
Accomplishment Instructions of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.21-162, Revision 1, dated September 
16, 2010. Application of additional sealant does not constitute 
terminating action for the repetitive detailed inspections required 
by paragraph (g) of this AD. Accomplishment of a repair as required 
by paragraph (g) of this AD terminates the repetitive inspection 
requirements of paragraph (g) of this AD.

(i) New Requirement of This AD: Inspection for Water Traps/Air Driers

    Within 12 months after the effective date of this AD, inspect 
the airplane to determine whether water traps/air driers are 
installed, in accordance with paragraph 2.C of BAE Systems 
(Operations) Limited Service Bulletin ISB.21-162, Revision 4, dated 
January 28, 2015 (``ISB.21-162 R4''). If there are no water traps/
air driers installed on an airplane, then no further inspections are 
required by this AD, except as required by paragraph (n) of this AD.

(j) New Requirement of This AD: Repetitive Inspections

    For airplanes that have water traps/air driers installed, 
determined as required by paragraph (i) of this AD: Within 12 months 
after the effective date of this AD, accomplish a detailed visual 
inspection for bulging, surface anomalies, and cracking of the 
external fuselage skin adjacent to the discharge valve outlets (one 
frame bay fore and aft, one stringer above and below), in accordance 
with the Accomplishment Instructions of paragraph 2.C. of ISB.21-162 
R4. Repeat the inspection of the external fuselage skin adjacent to 
the discharge valve outlets thereafter at intervals not to exceed 24 
months. Accomplishing an inspection required by this paragraph 
terminates the inspections required by paragraph (g) of this AD.

(k) New Requirement of This AD: Corrective Actions

    If, during any detailed visual inspection required by paragraph 
(j) of this AD, any bulging, surface anomalies, or cracking is 
found, before further flight, accomplish the applicable corrective 
action as specified in paragraphs (k)(1) and (k)(2) this AD.
    (1) If any bulging, surface anomalies, or cracking is found to 
be within the criteria as specified in the applicable service 
information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this 
AD, before further flight, repair in accordance with the 
Accomplishment Instructions of paragraph 2.G. of ISB.21-162 R4.
    (i) For Model BAe 146-100A and -200A airplanes, and Model Avro 
146-RJ70A and 146-RJ85A airplanes: Subject 53-00-00, ``Fuselage, 
General Description,'' of Chapter 53, ``Fuselage,'' of the BAE 
SYSTEMS BAe 146 Series/AVRO 146-RJ Series Structural Repair Manual 
for Series 100-200, Revision 68, dated October 15, 2014.
    (ii) For Model BAe 146-300A airplanes and Model Avro 146-RJ100A 
airplanes: Subject 53-00-00, ``Fuselage, General Description,'' of 
Chapter 53, ``Fuselage,'' of the BAe SYSTEMS BAE 146 Series/AVRO 
146-RJ Series Structural Repair Manual for Series 300, Revision 46, 
dated October 15, 2014.
    (2) If any bulging, surface anomalies, or cracking is found 
exceeding the criteria as specified in the applicable service 
information specified in paragraph (k)(1)(i) or (k)(1)(ii) 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 BAE Systems (Operations) Limited's 
EASA DOA.

(l) New Requirement of This AD: Application of Sealant

    Within 24 months after the effective date of this AD, unless a 
repair has already been accomplished as required by paragraph (k) of 
this AD, apply additional sealant, in accordance with the 
Accomplishment Instructions of paragraph 2.C.(3) of ISB.21-162 R4. 
Application of additional sealant on an airplane does not constitute 
terminating action for the repetitive inspections required by 
paragraph (j) of this AD for that airplane.

(m) New Terminating Action for Inspections Required by Paragraph (j) of 
This AD

    Accomplishment of a repair on the forward (FWD) or aft (AFT) 
position as required by paragraph (k) of this AD constitutes 
terminating action for the repetitive inspections required by 
paragraph (j) of this AD for that FWD or AFT position.

(n) New Requirement of This AD: Actions for Airplanes on Which Water 
Trap/Air Driers Are Installed After the Effective Date of This AD

    For airplanes that, determined as required by paragraph (i) of 
this AD, do not have water traps/air driers installed: If water 
traps/air driers are installed in service after the effective date 
of this AD, accomplish the actions required by paragraphs (j), (k), 
and (l) of this AD on that airplane within the applicable compliance 
times specified in paragraphs (j), (k), and (l) of this AD; except 
that where paragraphs (j) and (l) of this AD refer to ``the 
effective date of this AD,'' this AD requires compliance within the 
specified compliance time after the installation of water traps/air 
driers.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for inspections and sealant 
applications required by paragraphs (g) and (h) of this AD, if those 
actions were performed before September 18, 2012 (the effective date 
of AD 2012-16-08), using BAE SYSTEMS (OPERATIONS) LIMITED Inspection 
Service Bulletin ISB.21-162, dated June 7, 2010.
    (2) This paragraph provides credit for using criteria defined in 
the following subject of the applicable structural repair manual, as 
required by paragraphs (g)(1) and (g)(2) of this AD, if those 
criteria were used before September 18, 2012 (the effective date of 
AD 2012-16-08), using Subject 53-00-00, ``Fuselage, General--
Description,'' of Chapter 53, ``Fuselage,'' of the BAE SYSTEMS BAe 
146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 
100-200, Revision 65, dated September 15, 2010 (for Model 146-100A 
and -200A, and Avro 146-RJ70A and 146-RJ85A airplanes); or Subject 
53-00-00, ``Fuselage, General--Description,'' of Chapter 53, 
``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series 
Structural Repair Manual for Series 300, Revision 43, dated 
September 15, 2010 (for Model 146-300A and Avro 146-RJ100A 
airplanes).
    (3) This paragraph provides credit for actions required by 
paragraphs (i), (j), and (l) of this AD, if those actions were 
performed before the effective date of this AD using any of the 
service information specified in paragraphs (i)(3)(i) through 
(i)(3)(iv) of this AD.
    (i) BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.21-162, dated June 7, 2010.
    (ii) BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 1, dated September 16, 2010.
    (iii) BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 2, dated December 12, 2012.
    (iv) BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 3, dated January 15, 2013.

(p) Other FAA AD Provisions

    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: Theodore 
Thompson, Aerospace Engineer, telephone 425-227-1175; fax 425-227-
1149. Information may be emailed to: 9-ANM-116-AMOC-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: As of the effective date of 
this AD, for any requirement

[[Page 72561]]

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 European Aviation Safety Agency (EASA); or BAE Systems 
(Operations) Limited's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0180, dated August 28, 
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-2016-9186.
    (2) For service information identified in this AD, contact BAE 
Systems (Operations) Limited, Customer Information Department, 
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United 
Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email 
RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/RegionalAircraft/index.htm. 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 September 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-24201 Filed 10-19-16; 8:45 am]
 BILLING CODE 4910-13-P