81 FR 23208 - Airworthiness Directives; BAE SYSTEMS (Operations) Limited Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 76 (April 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 76 (April 20, 2016)
| Page Range | 23208-23212 | |
| FR Document | 2016-08957 |
[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)] [Proposed Rules] [Pages 23208-23212] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08957] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5465; Directorate Identifier 2015-NM-041-AD] RIN 2120-AA64 Airworthiness Directives; BAE SYSTEMS (Operations) Limited Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2010-10- 13, for all BAE SYSTEMS (Operations) Limited Model BAe 146 and Avro 146 series airplanes. AD 2010-10-13 currently requires repetitive inspections [[Page 23209]] of the wing fixed leading edge and front spar structure for corrosion and cracking, and repair if necessary. Since we issued AD 2010-10-13, the Design Approval Holder (DAH) has issued revised inspection procedures that eliminate a previously approved inspection procedure. This proposed AD would require revised inspection procedures. We are proposing this AD to detect and correct corrosion and cracking of the wing fixed leading edge and front spar structure, which could result in reduced structural integrity of the wing. DATES: We must receive comments on this proposed AD by June 6, 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. 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 [email protected]; 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- 5465; 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: Todd 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-2016-5465; Directorate Identifier 2015-NM-041-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 April 30, 2010, we issued AD 2010-10-13, Amendment 39-16292 (75 FR 27419, May 17, 2010) (``AD 2010-10-13''). AD 2010-10-13 requires actions intended to address an unsafe condition on all BAE SYSTEMS (Operations) Limited Model BAe 146 and Avro 146 series airplanes. Since we issued AD 2010-10-13, the DAH has issued revised inspection procedures that eliminates a previously approved inspection procedure. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0047, correction dated February 26, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition. The MCAI states: Corrosion of the wing fixed leading edge structure was detected on a BAe 146 aeroplane during removal of wing removable edge for a repair. The review of available scheduled tasks intended to detect environmental and fatigue deteriorations of the wing revealed that they may not have been sufficient to identify corrosion or fatigue damage in the affected structural area. This condition, if not detected and corrected, could lead to degradation of the structural integrity of the wing. To address this potential unsafe condition, EASA issued AD 2009- 0014 (http://ad.easa.europa.eu/blob/easa_ad_2009_0014_superseded.pdf/AD_2009-0014_1) [which corresponds to FAA AD 2010-10-13] to require repetitive inspections of fixed wing leading edge and front spar structure [for cracking and corrosion] [and repair if necessary] in accordance with BAE Systems (Operations) Ltd Inspection Service Bulletin (ISB) ISB.57-072 which incorporated two possible inspection procedures, either method 1, a combination of a detailed visual inspection (DVI) and a visual inspection (VI) after removal of the outer fixed leading edge only, or method 2, a DVI only, after removal of the inner, centre and outer fixed leading edges. Since that [EASA] AD was issued, BAE Systems (Operations) Ltd issued ISB.57-072 Revision 1 to correct a material reference number, Revision 2, which removed method 1 as an available inspection procedure to detect fatigue and environmental damage of the wing structure and Revision 3 to delete the requirement to install weights if the engines were removed when the leading edges were removed. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2009-0014, which is superseded, but requires accomplishment of the [repetitive] inspections in accordance with updated inspection procedures, i.e. method 2 only. This [EASA] AD is re-published to correct a typographical error in Table 1, restoring a compliance time as previously required by EASA AD 2009-0014. The repetitive inspection interval for the detailed visual inspection for cracking and corrosion of the wing fixed leading edge and front spar structure is: 12 years or 36,000 flight cycles, whichever occurs earlier, for airplanes on which the enhanced corrosion protection has not been accomplished. 6 years or 36,000 flight cycles, whichever occurs earlier, for airplanes on which the enhanced corrosion protection has been accomplished. 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- 5465. Related Service Information Under 1 CFR Part 51 BAE SYSTEMS (Operations) Limited has issued Service Bulletin ISB.57-072, Revision 3, dated August 31, 2010. The service information describes procedures for inspection and repair for cracking and corrosion of the wing fixed leading edge and front spar structure. 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. [[Page 23210]] 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 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 2010-10-13, and retained in this proposed AD take about 12 work-hours per product, and 1 work-hour per product for reporting, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2010-10-13 is $1,105 per product. The new requirements of this proposed AD add no additional economic burden. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. 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) 2010-10-13, Amendment 39-16292 (75 FR 27419, May 17, 2010), and adding the following new AD: BAE SYSTEMS (Operations) Limited: Docket No. FAA-2016-5465; Directorate Identifier 2015-NM-041-AD. (a) Comments Due Date We must receive comments by June 6, 2016. (b) Affected ADs This AD replaces AD 2010-10-13, Amendment 39-16292 (75 FR 27419, May 17, 2010) (``AD 2010-10-13''). (c) Applicability This AD applies to BAE SYSTEMS (Operations) Limited Model BAe 146-100A, -200A, and -300A series airplanes; and Model Avro 146- RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by revised inspection procedures issued by the Design Approval Holder. We are issuing this AD to detect and correct corrosion and cracking of the wing fixed leading edge and front spar structure, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Actions and Compliance, With Added Provision for Terminating Action This paragraph restates the requirements of paragraph (f) of AD 2010-10-13, with an added provision for terminating action. Accomplishing the initial inspection required by paragraph (j) of this AD terminates the requirements of paragraph (g) of this AD. (1) At the applicable time identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD: Perform a detailed visual inspection and visual inspection (Method 1) or a detailed visual inspection (Method 2) for cracking and corrosion of the wing fixed leading edge and front spar structure, in accordance with paragraph 2.C. or 2.D., as applicable, of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57- 072, Revision 1, dated September 25, 2008. (i) For airplanes with less than 9 years since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of the effective date of this AD: Within 18 months after June 21, 2010 (the effective date of AD 2010-10-13). (ii) For airplanes with 9 years or more, but less than 15 years, since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10- 13): Within 18 months after June 21, 2010, or within 16 years since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first. [[Page 23211]] (iii) For airplanes with 15 years or more since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10-13): Within 6 months after June 21, 2010. (2) After doing the initial inspection required by paragraph (g)(1) of this AD, at the applicable intervals specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, accomplish the repetitive inspections of the wing fixed leading edge and front spar structure for cracking and corrosion in the ``area of inspection'' specified in Table 1 of paragraph 1.D., ``Compliance,'' of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Do the inspections in accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method 2) of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Where previously applied, enhanced corrosion protection may then be re-applied, as an option, in accordance with paragraph 2.E. of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Perform the repetitive inspections at the times specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable. (i) For airplanes having enhanced corrosion protection that was applied during the previous inspection: Inspect at intervals not to exceed 144 months. (ii) For airplanes not having enhanced corrosion protection that was applied during the previous inspection: Inspect at intervals not to exceed 72 months. (3) After doing the initial inspection required by paragraph (g)(1) of this AD, at intervals not to exceed 36,000 flight cycles, accomplish fatigue inspections in accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method 2) of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. (4) If any cracking or corrosion is found during any inspection required by paragraph (g) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. (5) No repair terminates the inspection requirements of this AD. (6) Actions done before June 21, 2010 (the effective date of AD 2010-10-13), in accordance with BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, dated February 22, 2008, are considered acceptable for compliance with the corresponding actions specified in this AD. (7) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f)(1) of this AD to Customer Liaison, Customer Support (Building 37), BAE SYSTEMS (Operations) Limited, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; fax +44 (0) 1292 675432; email [email protected], at the applicable time specified in paragraphs (g)(7)(i) and (g)(7)(ii) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. (i) If the inspection was done on or after June 21, 2010 (the effective date of AD 2010-10-13): Submit the report within 30 days after the inspection. (ii) If the inspection was done before June 21, 2010 (the effective date of AD 2010-10-13): Submit the report within 30 days after June 21, 2010. (h) Retained Corrosion Protection Information, With No Changes This paragraph restates the corrosion protection information in Note 2 of AD 2010-10-13, with no changes. At the discretion of the airplane owner/operator, corrosion protection may be embodied on those areas subject to a detailed visual inspection, in accordance with paragraph 2.E. or paragraph 2.F. of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Embodiment of enhanced corrosion protection in accordance with paragraph 2.E. of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008, allows the interval of the repetitive inspection (as required by paragraph (g)(2) of this AD) to be extended in the area(s) of application in accordance with paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable. (i) Retained Inspection Information, With No Changes This paragraph restates the inspection information in Note 3 of AD 2010-10-13, with no changes. The inspections required by this AD prevail over the Maintenance Review Board Report (MRBR), Maintenance Planning Document (MPD), Corrosion Prevention and Control Program (CPCP), and Supplemental Structural Inspection Document (SSID) inspections defined in paragraph 1.C.(3) of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. (j) New Requirement of This AD: Repetitive Inspection At the applicable time identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD; or within 6 months after the effective date of this AD; whichever occurs later: Perform a detailed visual inspection for cracking and corrosion of the wing fixed leading edge and front spar structure, in accordance with paragraph 2.C. of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 3, dated August 31, 2010. Repeat the inspection thereafter at the applicable intervals specified in paragraph 1.D.2. of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 3, dated August 31, 2010. Accomplishing the initial inspection required by this paragraph terminates the requirements of paragraph (g) of this AD. (1) For airplanes with less than 9 years since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10-13): Within 18 months after June 21, 2010, or within 9 years since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs later. (2) For airplanes with 9 years or more, but less than 15 years, since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10- 13): Within 18 months after June 21, 2010, or within 16 years since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first. (3) For airplanes with 15 years or more since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of the June 21, 2010 (the effective date of AD 2010-10-13): Within 6 months after June 21, 2010. (k) New Requirement of This AD: Repair If any crack or corrosion are found during any inspection required by paragraph (j) of this AD: Before further flight, repair 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). (l) No Provisions for Terminating Action Accomplishment of any repair, as required by paragraph (k) of this AD, does not constitute terminating action for inspections required by this AD. (m) Credit for Previous Actions This paragraph provides credit for actions required by this AD, if those actions were performed before the effective date of this AD using BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, dated February 22, 2008; or BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. (n) 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: Todd 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. [[Page 23212]] Information may be emailed to: [email protected]. 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 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 BAE SYSTEMS (Operations) Limited's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0047, correction dated February 26, 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-2016-5465. (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 [email protected]; 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 March 26, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08957 Filed 4-19-16; 8:45 am] BILLING CODE 4910-13-P
![23208 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
(a) Comments Due Date 1,900 flight hours after June 9, 2011 (the Flight Standards District Office, as
We must receive comments by June 6, effective date of AD 2011–10–01, appropriate. If sending information directly
2016. Amendment 39–16682 (76 FR 25535, May 5, to the International Branch, send it to ATTN:
2011)) or after modification M0305 or Tom Rodriguez, Aerospace Engineer,
(b) Affected ADs Dassault Service Bulletin 7X–018, dated International Branch, ANM–116, Transport
This AD replaces AD 2011–10–01, March 6, 2009, has been done, whichever Airplane Directorate, FAA, 1601 Lind
Amendment 39–16682 (76 FR 25535, May 5, occurs later, do a functional test of the RAT Avenue SW., Renton, WA 98057–3356;
2011). This AD affects AD 2014–16–23, heater. Repeat the functional test of the RAT telephone 425–227–1137; fax 425–227–1149.
Amendment 39–17947 (79 FR 52545, heater thereafter at intervals not to exceed Information may be emailed to: 9-ANM-116-
September 4, 2014). 1,900 flight hours. AMOC-REQUESTS@faa.gov.
Note 1 to paragraph (g) of this AD: (2) Contacting the Manufacturer: For any
(c) Applicability requirement in this AD to obtain corrective
Additional guidance for doing the functional
This AD applies to Dassault Aviation test of the RAT heater required by paragraph actions from a manufacturer, the action must
Model FALCON 7X airplanes, certificated in (g) of this AD can be found in Task 24–50– be accomplished using a method approved
any category, all serial numbers. 25–720–801, Functional Test of the RAT by the Manager, International Branch, ANM–
(d) Subject Heater, dated January 16, 2009, of the 116, Transport Airplane Directorate, FAA; or
Dassault FALCON 7X Aircraft Maintenance EASA; or Dassault Aviation’s EASA DOA. If
Air Transport Association (ATA) of Manual (AMM). approved by the DOA, the approval must
America Code 05, Time Limits/Maintenance include the DOA-authorized signature.
Checks. (h) New Requirement of This AD: Revise the
Maintenance or Inspection Program (l) Related Information
(e) Reason
Within 30 days after the effective date of (1) Refer to Mandatory Continuing
This AD was prompted by a revision of an Airworthiness Information (MCAI) EASA AD
this AD, revise the maintenance or inspection
airworthiness limitations items (ALI) 2015–0095, dated May 29, 2015, for related
document, which introduces new and more program, as applicable, by incorporating the
information specified in Chapter 5–40–00, information. You may examine the MCAI on
restrictive maintenance requirements and the Internet at http://www.regulations.gov by
airworthiness limitations for airplane Airworthiness Limitations, DGT 107838,
Revision 4, dated February 2, 2015, of the searching for and locating Docket No. FAA–
structures and systems. We are issuing this 2016–5464.
AD to prevent reduced structural integrity Dassault Falcon 7X Maintenance Manual
(MM). The initial compliance times for the (2) For service information identified in
and reduced control of these airplanes due to this AD, contact Dassault Falcon Jet
the failure of system components. tasks specified in Chapter 5–40–00,
Airworthiness Limitations, DGT 107838, Corporation, Teterboro Airport, P.O. Box
(f) Compliance Revision 4, dated February 2, 2015, of the 2000, South Hackensack, NJ 07606;
Dassault Falcon 7X MM are at the applicable telephone: 201–440–6700; Internet: http://
Comply with this AD within the
compliance times specified in Chapter 5–40– www.dassaultfalcon.com. You may view this
compliance times specified, unless already
done. 00, Airworthiness Limitations, DGT 107838, service information at the FAA, Transport
Revision 4, dated February 2, 2015, of the Airplane Directorate, 1601 Lind Avenue SW.,
(g) Retained Functional Test of the Ram Air Dassault Falcon 7X MM, or within 30 days Renton, WA. For information on the
Turbine (RAT) Heater With New after the effective date of this AD, whichever availability of this material at the FAA, call
Terminating Action and With Specific occurs later. 425–227–1221.
Delegation Approval Language
(i) Terminating Actions Issued in Renton, Washington, on April 13,
This paragraph restates the requirements of 2016.
paragraph (g) of AD 2011–10–01, (1) Accomplishment of the revision
required by paragraph (h) of this AD Victor Wicklund,
Amendment 39–16682 (76 FR 25535, May 5,
2011), with new terminating action and with terminates the requirements of paragraph (g) Acting Manager, Transport Airplane
specific delegation approval language. At the of this AD. Directorate, Aircraft Certification Service.
applicable times specified in paragraph (g)(1) (2) Accomplishment of the revision [FR Doc. 2016–09005 Filed 4–19–16; 8:45 am]
or (g)(2) of this AD, do a functional test of required by paragraph (h) of this AD BILLING CODE 4910–13–P
the RAT heater using a method approved by terminates the requirements of paragraph (q)
either the Manager, International Branch, of AD 2014–16–23, Amendment 39–17947
ANM–116, Transport Airplane Directorate, (79 FR 52545, September 4, 2014). DEPARTMENT OF TRANSPORTATION
FAA; or the European Aviation Safety
(j) No Alternative Actions, Intervals, and/or
Agency (EASA); or Dassault Aviation’s EASA Federal Aviation Administration
Critical Design Configuration Control
Design Organization Approval (DOA). Repeat
Limitations (CDCCLs)
the functional test of the RAT heater
thereafter at the applicable time specified in After the maintenance or inspection 14 CFR Part 39
paragraph (g)(1) or (g)(2) of this AD until the program, as applicable, has been revised as [Docket No. FAA–2016–5465; Directorate
revision required by paragraph (h) of this AD required by paragraph (h) of this AD, no Identifier 2015–NM–041–AD]
is done. If any functional test fails, before alternative actions (e.g., inspections),
further flight, repair using a method intervals, and/or CDCCLs may be used unless RIN 2120–AA64
approved by either the Manager, the actions, intervals, and/or CDCCLs are
International Branch, ANM–116, Transport approved as an alternative method of Airworthiness Directives; BAE
Airplane Directorate, FAA; or EASA; or compliance (AMOC) in accordance with the SYSTEMS (Operations) Limited
Dassault Aviation’s EASA DOA. procedures specified in paragraph (k)(1) of Airplanes
(1) For FALCON 7X airplanes on which this AD.
modification M0305 has not been done and AGENCY: Federal Aviation
(k) Other FAA AD Provisions
on which Dassault Service Bulletin 7X–018, Administration (FAA), DOT.
dated March 6, 2009, has not been done: The following provisions also apply to this
ACTION: Notice of proposed rulemaking
AD:
Lhorne on DSK5TPTVN1PROD with PROPOSALS
Within 650 flight hours after the effective
(1) Alternative Methods of Compliance (NPRM).
date of this AD, do a functional test of the
RAT heater and repeat the functional test of (AMOCs): The Manager, International
SUMMARY: We propose to supersede
the RAT heater thereafter at intervals not to Branch, ANM–116, Transport Airplane
exceed 650 flight hours. Directorate, FAA, has the authority to Airworthiness Directive (AD) 2010–10–
(2) For FALCON 7X airplanes on which approve AMOCs for this AD, if requested 13, for all BAE SYSTEMS (Operations)
modification M0305 has been done or on using the procedures found in 14 CFR 39.19. Limited Model BAe 146 and Avro 146
which Dassault Service Bulletin 7X–018, In accordance with 14 CFR 39.19, send your series airplanes. AD 2010–10–13
dated March 6, 2009, has been done: Within request to your principal inspector or local currently requires repetitive inspections
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![Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules 23209
of the wing fixed leading edge and front be available in the AD docket shortly To address this potential unsafe condition,
spar structure for corrosion and after receipt. EASA issued AD 2009–0014 (http://
cracking, and repair if necessary. Since ad.easa.europa.eu/blob/easa_ad_2009_0014_
FOR FURTHER INFORMATION CONTACT:
we issued AD 2010–10–13, the Design superseded.pdf/AD_2009–0014_1) [which
Todd Thompson, Aerospace Engineer, corresponds to FAA AD 2010–10–13] to
Approval Holder (DAH) has issued International Branch, ANM–116, require repetitive inspections of fixed wing
revised inspection procedures that Transport Airplane Directorate, FAA, leading edge and front spar structure [for
eliminate a previously approved 1601 Lind Avenue SW., Renton, WA cracking and corrosion] [and repair if
inspection procedure. This proposed 98057–3356; telephone 425–227–1175; necessary] in accordance with BAE Systems
AD would require revised inspection fax 425–227–1149. (Operations) Ltd Inspection Service Bulletin
procedures. We are proposing this AD to SUPPLEMENTARY INFORMATION: (ISB) ISB.57–072 which incorporated two
detect and correct corrosion and possible inspection procedures, either
cracking of the wing fixed leading edge Comments Invited method 1, a combination of a detailed visual
and front spar structure, which could inspection (DVI) and a visual inspection (VI)
We invite you to send any written after removal of the outer fixed leading edge
result in reduced structural integrity of relevant data, views, or arguments about only, or method 2, a DVI only, after removal
the wing. this proposed AD. Send your comments of the inner, centre and outer fixed leading
DATES: We must receive comments on to an address listed under the edges.
this proposed AD by June 6, 2016. ADDRESSES section. Include ‘‘Docket No. Since that [EASA] AD was issued, BAE
ADDRESSES: You may send comments by FAA–2016–5465; Directorate Identifier Systems (Operations) Ltd issued ISB.57–072
any of the following methods: 2015–NM–041–AD’’ at the beginning of Revision 1 to correct a material reference
number, Revision 2, which removed method
• Federal eRulemaking Portal: Go to your comments. We specifically invite
1 as an available inspection procedure to
http://www.regulations.gov. Follow the comments on the overall regulatory,
detect fatigue and environmental damage of
instructions for submitting comments. economic, environmental, and energy the wing structure and Revision 3 to delete
• Fax: 202–493–2251. aspects of this proposed AD. We will the requirement to install weights if the
• Mail: U.S. Department of consider all comments received by the engines were removed when the leading
Transportation, Docket Operations, M– closing date and may amend this edges were removed.
30, West Building Ground Floor, Room proposed AD based on those comments. For the reasons described above, this
W12–140, 1200 New Jersey Avenue SE., We will post all comments we [EASA] AD retains the requirements of EASA
Washington, DC 20590. receive, without change, to http:// AD 2009–0014, which is superseded, but
requires accomplishment of the [repetitive]
• Hand Delivery: U.S. Department of www.regulations.gov, including any
personal information you provide. We inspections in accordance with updated
Transportation, Docket Operations, M– inspection procedures, i.e. method 2 only.
30, West Building Ground Floor, Room will also post a report summarizing each This [EASA] AD is re-published to correct
W12–140, 1200 New Jersey Avenue SE., substantive verbal contact we receive a typographical error in Table 1, restoring a
Washington, DC, between 9 a.m. and 5 about this proposed AD. compliance time as previously required by
p.m., Monday through Friday, except Discussion EASA AD 2009–0014.
Federal holidays.
For service information identified in On April 30, 2010, we issued AD The repetitive inspection interval for
this NPRM, contact BAE Systems 2010–10–13, Amendment 39–16292 (75 the detailed visual inspection for
(Operations) Limited, Customer FR 27419, May 17, 2010) (‘‘AD 2010– cracking and corrosion of the wing fixed
Information Department, Prestwick 10–13’’). AD 2010–10–13 requires leading edge and front spar structure is:
International Airport, Ayrshire, KA9 actions intended to address an unsafe • 12 years or 36,000 flight cycles,
2RW, Scotland, United Kingdom; condition on all BAE SYSTEMS whichever occurs earlier, for airplanes
telephone +44 1292 675207; fax +44 (Operations) Limited Model BAe 146 on which the enhanced corrosion
1292 675704; email RApublications@ and Avro 146 series airplanes. protection has not been accomplished.
baesystems.com; Internet http:// Since we issued AD 2010–10–13, the
DAH has issued revised inspection • 6 years or 36,000 flight cycles,
www.baesystems.com/Businesses/ whichever occurs earlier, for airplanes
RegionalAircraft/index.htm. You may procedures that eliminates a previously
approved inspection procedure. on which the enhanced corrosion
view this referenced service information protection has been accomplished.
at the FAA, Transport Airplane The European Aviation Safety Agency
Directorate, 1601 Lind Avenue SW., (EASA), which is the Technical Agent You may examine the MCAI in the
Renton, WA. For information on the for the Member States of the European AD docket on the Internet at http://
availability of this material at the FAA, Union, has issued EASA Airworthiness www.regulations.gov by searching for
call 425–227–1221. Directive 2014–0047, correction dated and locating Docket No. FAA–2016–
February 26, 2015 (referred to after this 5465.
Examining the AD Docket as the Mandatory Continuing
Related Service Information Under 1
You may examine the AD docket on Airworthiness Information, or ‘‘the
CFR Part 51
the Internet at http:// MCAI’’), to correct an unsafe condition.
www.regulations.gov by searching for The MCAI states: BAE SYSTEMS (Operations) Limited
and locating Docket No. FAA–2016– Corrosion of the wing fixed leading edge has issued Service Bulletin ISB.57–072,
5465; or in person at the Docket structure was detected on a BAe 146 Revision 3, dated August 31, 2010. The
Management Facility between 9 a.m. aeroplane during removal of wing removable service information describes
Lhorne on DSK5TPTVN1PROD with PROPOSALS
and 5 p.m., Monday through Friday, edge for a repair. The review of available procedures for inspection and repair for
except Federal holidays. The AD docket scheduled tasks intended to detect cracking and corrosion of the wing fixed
contains this proposed AD, the environmental and fatigue deteriorations of leading edge and front spar structure.
the wing revealed that they may not have
regulatory evaluation, any comments been sufficient to identify corrosion or
This service information is reasonably
received, and other information. The fatigue damage in the affected structural area. available because the interested parties
street address for the Docket Operations This condition, if not detected and have access to it through their normal
office (telephone 800–647–5527) is in corrected, could lead to degradation of the course of business or by the means
the ADDRESSES section. Comments will structural integrity of the wing. identified in the ADDRESSES section.
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![23210 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
FAA’s Determination and Requirements the FAA Administrator. ‘‘Subtitle VII: BAE SYSTEMS (Operations) Limited: Docket
of This Proposed AD Aviation Programs,’’ describes in more No. FAA–2016–5465; Directorate
detail the scope of the Agency’s Identifier 2015–NM–041–AD.
This product has been approved by
the aviation authority of another authority. (a) Comments Due Date
country, and is approved for operation We are issuing this rulemaking under We must receive comments by June 6,
in the United States. Pursuant to our the authority described in ‘‘Subtitle VII, 2016.
bilateral agreement with the State of Part A, Subpart III, Section 44701:
General requirements.’’ Under that (b) Affected ADs
Design Authority, we have been notified This AD replaces AD 2010–10–13,
of the unsafe condition described in the section, Congress charges the FAA with
promoting safe flight of civil aircraft in Amendment 39–16292 (75 FR 27419, May 17,
MCAI and service information 2010) (‘‘AD 2010–10–13’’).
referenced above. We are proposing this air commerce by prescribing regulations
AD because we evaluated all pertinent for practices, methods, and procedures (c) Applicability
information and determined an unsafe the Administrator finds necessary for This AD applies to BAE SYSTEMS
condition exists and is likely to exist or safety in air commerce. This regulation (Operations) Limited Model BAe 146–100A,
develop on other products of these same is within the scope of that authority –200A, and –300A series airplanes; and
because it addresses an unsafe condition Model Avro 146–RJ70A, 146–RJ85A, and
type designs. 146–RJ100A airplanes; certificated in any
that is likely to exist or develop on
Costs of Compliance products identified in this rulemaking category, all serial numbers.
We estimate that this proposed AD action. (d) Subject
affects 4 airplanes of U.S. registry. Regulatory Findings Air Transport Association (ATA) of
The actions required by AD 2010–10– America Code 57, Wings.
13, and retained in this proposed AD We determined that this proposed AD
would not have federalism implications (e) Reason
take about 12 work-hours per product,
under Executive Order 13132. This This AD was prompted by revised
and 1 work-hour per product for inspection procedures issued by the Design
reporting, at an average labor rate of $85 proposed AD would not have a
substantial direct effect on the States, on Approval Holder. We are issuing this AD to
per work-hour. Based on these figures, detect and correct corrosion and cracking of
the estimated cost of the actions that are the relationship between the national the wing fixed leading edge and front spar
required by AD 2010–10–13 is $1,105 Government and the States, or on the structure, which could result in reduced
per product. distribution of power and structural integrity of the airplane.
The new requirements of this responsibilities among the various
(f) Compliance
proposed AD add no additional levels of government.
For the reasons discussed above, I Comply with this AD within the
economic burden. compliance times specified, unless already
We have received no definitive data certify this proposed regulation:
1. Is not a ‘‘significant regulatory done.
that would enable us to provide cost
estimates for the on-condition actions action’’ under Executive Order 12866; (g) Retained Actions and Compliance, With
specified in this proposed AD. 2. Is not a ‘‘significant rule’’ under the Added Provision for Terminating Action
DOT Regulatory Policies and Procedures This paragraph restates the requirements of
Paperwork Reduction Act (44 FR 11034, February 26, 1979); paragraph (f) of AD 2010–10–13, with an
A federal agency may not conduct or 3. Will not affect intrastate aviation in added provision for terminating action.
sponsor, and a person is not required to Alaska; and Accomplishing the initial inspection
4. Will not have a significant required by paragraph (j) of this AD
respond to, nor shall a person be subject terminates the requirements of paragraph (g)
to penalty for failure to comply with a economic impact, positive or negative,
on a substantial number of small entities of this AD.
collection of information subject to the (1) At the applicable time identified in
requirements of the Paperwork under the criteria of the Regulatory paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
Reduction Act unless that collection of Flexibility Act. this AD: Perform a detailed visual inspection
information displays a current valid List of Subjects in 14 CFR Part 39 and visual inspection (Method 1) or a
OMB control number. The control detailed visual inspection (Method 2) for
Air transportation, Aircraft, Aviation cracking and corrosion of the wing fixed
number for the collection of information
safety, Incorporation by reference, leading edge and front spar structure, in
required by this AD is 2120–0056. The accordance with paragraph 2.C. or 2.D., as
Safety.
paperwork cost associated with this AD applicable, of the Accomplishment
has been detailed in the Costs of The Proposed Amendment Instructions of BAE SYSTEMS (Operations)
Compliance section of this document Accordingly, under the authority Limited Inspection Service Bulletin ISB.57–
and includes time for reviewing 072, Revision 1, dated September 25, 2008.
delegated to me by the Administrator, (i) For airplanes with less than 9 years
instructions, as well as completing and the FAA proposes to amend 14 CFR part
reviewing the collection of information. since date of issuance of the original
39 as follows: airworthiness certificate or the date of
Therefore, all reporting associated with issuance of the original export certificate of
this AD is mandatory. Comments PART 39—AIRWORTHINESS airworthiness as of the effective date of this
concerning the accuracy of this burden DIRECTIVES AD: Within 18 months after June 21, 2010
and suggestions for reducing the burden (the effective date of AD 2010–10–13).
should be directed to the FAA at 800 ■ 1. The authority citation for part 39 (ii) For airplanes with 9 years or more, but
Independence Ave. SW., Washington, continues to read as follows: less than 15 years, since date of issuance of
Lhorne on DSK5TPTVN1PROD with PROPOSALS
DC 20591, ATTN: Information the original airworthiness certificate or the
Authority: 49 U.S.C. 106(g), 40113, 44701.
date of issuance of the original export
Collection Clearance Officer, AES–200.
§ 39.13 [Amended] certificate of airworthiness as of June 21,
Authority for This Rulemaking 2010 (the effective date of AD 2010–10–13):
■ 2. The FAA amends § 39.13 by Within 18 months after June 21, 2010, or
Title 49 of the United States Code removing Airworthiness Directive (AD) within 16 years since date of issuance of the
specifies the FAA’s authority to issue 2010–10–13, Amendment 39–16292 (75 original airworthiness certificate or the date
rules on aviation safety. Subtitle I, FR 27419, May 17, 2010), and adding of issuance of the original export certificate
section 106, describes the authority of the following new AD: of airworthiness, whichever occurs first.
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![23212 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
Information may be emailed to: 9-ANM-116- DEPARTMENT OF TRANSPORTATION FOR FURTHER INFORMATION CONTACT:
AMOC-REQUESTS@faa.gov. Before using Patrick Farina, Aerospace Engineer,
any approved AMOC, notify your appropriate Federal Aviation Administration Cabin Safety Branch, ANM–150L, FAA,
principal inspector, or lacking a principal Los Angeles Aircraft Certification Office
inspector, the manager of the local flight 14 CFR Part 39
standards district office/certificate holding
(ACO), 3960 Paramount Boulevard,
district office. The AMOC approval letter [Docket No. FAA–2016–5595; Directorate Lakewood, CA 90712–4137; phone:
must specifically reference this AD. Identifier 2015–NM–087–AD] 562–627–5344; fax: 562–627–5210;
(2) Contacting the Manufacturer: As of the email: patrick.farina@faa.gov.
RIN 2120–AA64
effective date of this AD, for any requirement SUPPLEMENTARY INFORMATION:
in this AD to obtain corrective actions from
a manufacturer, the action must be
Airworthiness Directives; Zodiac Seats Comments Invited
accomplished using a method approved by California LLC Seating Systems
We invite you to send any written
the Manager, International Branch, ANM– AGENCY: Federal Aviation relevant data, views, or arguments about
116, Transport Airplane Directorate, FAA; or
Administration (FAA), DOT. this proposal. Send your comments to
the EASA; or BAE SYSTEMS (Operations)
Limited’s EASA DOA. If approved by the ACTION: Notice of proposed rulemaking an address listed under the ADDRESSES
DOA, the approval must include the DOA- (NPRM). section. Include ‘‘Docket No. FAA–
authorized signature. 2016–5595; Directorate Identifier 2015–
(3) Reporting Requirements: A federal SUMMARY: We propose to adopt a new NM–087–AD’’ at the beginning of your
agency may not conduct or sponsor, and a airworthiness directive (AD) for certain comments. We specifically invite
person is not required to respond to, nor Zodiac Seats California LLC seating comments on the overall regulatory,
shall a person be subject to a penalty for systems. This proposed AD was economic, environmental, and energy
failure to comply with a collection of prompted by a determination that the aspects of this proposed AD. We will
information subject to the requirements of affected seating systems may cause consider all comments received by the
the Paperwork Reduction Act unless that serious injury to the occupant during
collection of information displays a current closing date and may amend this
forward impacts when subjected to proposed AD because of those
valid OMB Control Number. The OMB
Control Number for this information certain inertia forces. This proposed AD comments.
collection is 2120–0056. Public reporting for would require removing affected seating We will post all comments we
this collection of information is estimated to systems. We are proposing this AD to receive, without change, to http://
be approximately 5 minutes per response, prevent serious injury to the occupant www.regulations.gov, including any
including the time for reviewing instructions, during forward impacts in emergency personal information you provide. We
completing and reviewing the collection of landing conditions. will also post a report summarizing each
information. All responses to this collection DATES: We must receive comments on substantive verbal contact we receive
of information are mandatory. Comments
this proposed AD by June 6, 2016. about this proposed AD.
concerning the accuracy of this burden and
suggestions for reducing the burden should ADDRESSES: You may send comments, Discussion
be directed to the FAA at: 800 Independence using the procedures found in 14 CFR
Ave. SW., Washington, DC 20591, Attn: 11.43 and 11.45, by any of the following We determined that occupants of
Information Collection Clearance Officer, methods: certain Zodiac Seats California LLC
AES–200. • Federal eRulemaking Portal: Go to seating systems having model numbers
http://www.regulations.gov. Follow the 4157, 4170, and 4184, may experience
(o) Related Information
instructions for submitting comments. serious injury during forward impacts
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA • Fax: 202–493–2251. when subjected to inertia forces as
Airworthiness Directive 2014–0047, • Mail: U.S. Department of defined by 14 CFR 25.561 and 14 CFR
correction dated February 26, 2015, for Transportation, Docket Operations, M– 25.562 (and thus are noncompliant with
related information. This MCAI may be 30, West Building Ground Floor, Room 14 CFR 25.785). The affected seating
found in the AD docket on the Internet at W12–140, 1200 New Jersey Avenue SE., systems are installed on, but not limited
http://www.regulations.gov by searching for Washington, DC 20590. to, various transport category airplanes.
and locating Docket No. FAA–2016–5465. • Hand Delivery: Deliver to Mail The impact of the head onto a typical
(2) For service information identified in address above between 9 a.m. and 5 transport passenger seat back during
this AD, contact BAE Systems (Operations) p.m., Monday through Friday, except seat qualification testing normally
Limited, Customer Information Department, results in an initial contact followed by
Federal holidays.
Prestwick International Airport, Ayrshire, an unimpeded sliding motion down the
KA9 2RW, Scotland, United Kingdom; Examining the AD Docket
telephone +44 1292 675207; fax +44 1292
back of the seat. That type of interaction
675704; email RApublications@ You may examine the AD docket on does not typically result in excessive
baesystems.com; Internet http:// the Internet at http:// neck loading or direct concentrated
www.baesystems.com/Businesses/ www.regulations.gov by searching for loading on the neck. The design of the
RegionalAircraft/index.htm. You may view and locating Docket No. FAA–2016– affected seating systems introduce new
this service information at the FAA, 5595; or in person at the Docket injury mechanisms such that the chin
Transport Airplane Directorate, 1601 Lind Management Facility between 9 a.m. can catch on the seat, causing high neck
Avenue SW., Renton, WA. For information and 5 p.m., Monday through Friday, bending loads and direct concentrated
on the availability of this material at the loading on the neck. This interaction
except Federal holidays. The AD docket
FAA, call 425–227–1221.
Lhorne on DSK5TPTVN1PROD with PROPOSALS
contains this proposed AD, the between the head and the seat during
Issued in Renton, Washington, on March regulatory evaluation, any comments forward impacts can result in serious
26, 2016. received, and other information. The injury to the occupant.
Jeffrey E. Duven, street address for the Docket Office 14 CFR 25.785 states that seat designs
Manager, Transport Airplane Directorate, (phone: 800–647–5527) is in the cannot cause a serious injury to the
Aircraft Certification Service. ADDRESSES section. Comments will be occupant when making proper use of
[FR Doc. 2016–08957 Filed 4–19–16; 8:45 am] available in the AD docket shortly after the seat and restraint and subjected to
BILLING CODE 4910–13–P receipt. the inertia forces specified in 14 CFR
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Document Created: 2016-04-20 01:51:58
Document Modified: 2016-04-20 01:51:58
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 6, 2016. | |
| Contact | Todd 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. | |
| FR Citation | 81 FR 23208 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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