Airworthiness Directives; Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company) Airplanes, 3348-3350 [2016-00951]

Download as PDF 3348 § 39.13 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–10–03, Amendment 39–18158 (80 FR 30608, May 29, 2015), and adding the following new AD: ■ Airbus: Docket No. FAA–2016–0459; Directorate Identifier 2015–NM–081–AD. (a) Comments Due Date We must receive comments by March 7, 2016. (b) Affected ADs This AD replaces 2015–10–03, Amendment 39–18158 (80 FR 30608, May 29, 2015). (c) Applicability This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, except airplanes on which an upper cardan pin on a main landing gear (MLG) has never been replaced or reinstalled since first entry into service of the airplane. (1) Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, all manufacturer serial numbers . (2) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes, all manufacturer serial numbers. (3) Airbus Model A340–541 and –642 airplanes, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by a report that an MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants. jstallworth on DSK7TPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition For the purpose of this AD, an upper cardan pin on a MLG is affected if it has been installed as a replacement part, or reinstalled since first entry of the airplane into service, and if the installation was accomplished using the applicable airplane maintenance manual at a revision level prior to October 1, 2014. (h) Inspection and Replacement (1) For an affected upper cardan pin on an MLG: Before exceeding 96 months since its latest installation on an airplane, or within 12 months after the effective date of this AD, whichever occurs later, do a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread VerDate Sep<11>2014 15:09 Jan 20, 2016 Jkt 238001 damage, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (i) of this AD. (2) If, during the detailed inspection specified in paragraph (h)(1) of this AD, any corrosion, pitting, or thread damage is found, before further flight, replace the upper cardan pin and/or nut, as applicable, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (i) of this AD. (i) Applicable Service Information Do the actions required by paragraph (h) of this AD in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (1) Airbus Service Bulletin A330–32–3269, dated February 17, 2015 (for Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes). (2) Airbus Service Bulletin A340–32–4301, dated February 17, 2015 (for Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes). (3) Airbus Service Bulletin A340–32–5115, dated February 17, 2015 (for Airbus Model A340–541 and –642 airplanes). (j) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; 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 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 Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0079, dated May 7, 2015, for related information. This PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2016–0459. (2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on January 8, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–00944 Filed 1–20–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–0460; Directorate Identifier 2015–NM–078–AD] RIN 2120–AA64 Airworthiness Directives; Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Beechcraft Corporation Model BAe.125 series 1000A and 1000B airplanes and Model Hawker 1000 airplanes. This proposed AD was prompted by reports of inadvertent stowage of the thrust reversers, which can result in high forward engine thrust even though the throttle is commanding reverse thrust. This proposed AD would require installing kits that include relays, associated wiring, and a thrust reverser fail annunciator. We are proposing this AD to prevent inadvertent stowage of the thrust reversers, which could cause a runway overrun during a rejected takeoff or landing, and consequent structural failure and possible injury to occupants. DATES: We must receive comments on this proposed AD by March 7, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR SUMMARY: E:\FR\FM\21JAP1.SGM 21JAP1 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201–0085; telephone 316–676–8238; fax 316–671–2540; email tmdc@beechcraft.com; Internet http:// pubs.beechcraft.com. You may view this referenced service information at 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– 0460; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jeffrey Englert, Aerospace Engineer, Mechanical Systems and Propulsion Branch, ACE–116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Dwight D. Eisenhower National Airport, Wichita, KS 67209; phone: 316–946–4167; fax: 316–946–4107; email: jeffrey.englert@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2016–0460; Directorate Identifier 2015– NM–078–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of inadvertent stowage of the thrust reversers, which can result in high forward engine thrust even though the throttle is commanding reverse thrust. These reports were on another type of airplane that utilizes a similar engine and thrust reverser system. The root cause is incorrect software logic within the engine’s electronic control unit. This condition, if not corrected, could result in inadvertent stowage of the thrust reversers, which could cause a runway overrun during a rejected takeoff or during landing, and consequent structural failure and possible injury to occupants. 3349 Related Service Information Under 1 CFR Part 51 We reviewed Beechcraft Mandatory Service Bulletin 78–4133, dated May 2015. The service information describes procedures for installing kits having part numbers 140–9005 and 140–9006, which include relays, associated wiring, and a thrust reverser fail annunciator. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ Differences Between This Proposed AD and the Service Information Although Beechcraft Mandatory Service Bulletin 78–4133, dated May 2015, specifies that ‘‘Should any difficulty be encountered in accomplishing this Service Bulletin, contact Beechcraft Corporation,’’ this proposed AD would require operators to resolve difficulties in accordance with a method approved by the FAA. Costs of Compliance We estimate that this proposed AD affects 38 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Installation ........................................ 340 work-hours × $85 per hour = $28,900 ................... $100,000 $128,900 $4,898,200 jstallworth on DSK7TPTVN1PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. VerDate Sep<11>2014 15:09 Jan 20, 2016 Jkt 238001 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 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 E:\FR\FM\21JAP1.SGM 21JAP1 3350 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company): Docket No. FAA–2016–0460; Directorate Identifier 2015–NM–078–AD. (a) Comments Due Date We must receive comments by March 7, 2016. jstallworth on DSK7TPTVN1PROD with PROPOSALS (b) Affected ADs None. (c) Applicability This AD applies to Beechcraft Corporation (type certificate previously held by Hawker Beechcraft Corporation; Raytheon Aircraft Company) airplanes, certificated in any category, as identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model BAe.125 series 1000A and 1000B airplanes, serial numbers 258151, 258159, and 259004 through 259042 inclusive. (2) Model Hawker 1000 airplanes, serial numbers 259003 and 259043 through 259052 inclusive. VerDate Sep<11>2014 15:09 Jan 20, 2016 Jkt 238001 (d) Subject Air Transport Association (ATA) of America Code 78, Exhaust. (e) Unsafe Condition This AD was prompted by reports of inadvertent stowage of the thrust reversers, which can result in high forward engine thrust even though the throttle is commanding reverse thrust. We are issuing this AD to prevent inadvertent stowage of the thrust reversers, which could cause a runway overrun during a rejected takeoff or landing, and consequent structural failure and possible injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. http://pubs.beechcraft.com. You may view this referenced service information at 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 January 8, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–00951 Filed 1–20–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration (g) Installation Within 600 flight hours or 12 months after the effective date of this AD, whichever occurs first: Install kits having part numbers 140–9005 and 140–9006, in accordance with the Accomplishment Instructions of Beechcraft Mandatory Service Bulletin 78– 4133, dated May 2015, except as specified in paragraph (h) of this AD. 14 CFR Part 39 (h) Exception to Service Information A note in the Accomplishment Instructions of Beechcraft Mandatory Service Bulletin 78– 4133, dated May 2015, instructs operators to contact Beechcraft Corporation if any difficulty is encountered in accomplishing the service bulletin. However, any deviation from the actions required by paragraph (g) of this AD must be approved as an alternative method of compliance (AMOC) under paragraph (i)(1) of this AD. AGENCY: (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita 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 (j)(1) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (j) Related Information (1) For more information about this AD, contact Jeffrey Englert, Aerospace Engineer, Mechanical Systems and Propulsion Branch, ACE–116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Dwight D. Eisenhower National Airport, Wichita, KS 67209; phone: 316–946– 4167; fax: 316–946–4107; email: jeffrey.englert@faa.gov. (2) For service information identified in this AD, contact Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201– 0085; telephone 316–676–8238; fax 316–671– 2540; email tmdc@beechcraft.com; Internet PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 [Docket No. FAA–2016–0457; Directorate Identifier 2015–NM–084–AD] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to supersede Airworthiness Directive (AD) 2012–11– 15, for all BAE Systems (Operations) Limited Model 4101 airplanes. AD 2012–11–15 currently requires a onetime detailed inspection for cracks, corrosion, and other defects of the rear face of the wing rear spar, and repair if necessary. Since we issued AD 2012– 11–15, we received new reports of cracking found in the wing rear spar and technical analysis results confirmed that the crack initiation and propagation are due to fatigue, with no indication of any other crack initiation mechanism (e.g. stress corrosion). This proposed AD would require repetitive detailed inspections, and repair if necessary. We are proposing this AD to detect and correct cracking in the wing rear spar, which could propagate to a critical length, possibly affecting the structural integrity of the area and resulting in a fuel tank rupture, with consequent damage to the airplane and possible injury to its occupants. DATES: We must receive comments on this proposed AD by March 7, 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– SUMMARY: E:\FR\FM\21JAP1.SGM 21JAP1

Agencies

[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Proposed Rules]
[Pages 3348-3350]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00951]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0460; Directorate Identifier 2015-NM-078-AD]
RIN 2120-AA64


Airworthiness Directives; Beechcraft Corporation (Type 
Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon 
Aircraft Company) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Beechcraft Corporation Model BAe.125 series 1000A and 1000B 
airplanes and Model Hawker 1000 airplanes. This proposed AD was 
prompted by reports of inadvertent stowage of the thrust reversers, 
which can result in high forward engine thrust even though the throttle 
is commanding reverse thrust. This proposed AD would require installing 
kits that include relays, associated wiring, and a thrust reverser fail 
annunciator. We are proposing this AD to prevent inadvertent stowage of 
the thrust reversers, which could cause a runway overrun during a 
rejected takeoff or landing, and consequent structural failure and 
possible injury to occupants.

DATES: We must receive comments on this proposed AD by March 7, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR

[[Page 3349]]

11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, Beechcraft 
Corporation, TMDC, P.O. Box 85, Wichita, KS 67201-0085; telephone 316-
676-8238; fax 316-671-2540; email tmdc@beechcraft.com; Internet http://pubs.beechcraft.com. You may view this referenced service information 
at 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-
0460; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jeffrey Englert, Aerospace Engineer, 
Mechanical Systems and Propulsion Branch, ACE-116W, FAA, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Dwight D. 
Eisenhower National Airport, Wichita, KS 67209; phone: 316-946-4167; 
fax: 316-946-4107; email: jeffrey.englert@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-0460; 
Directorate Identifier 2015-NM-078-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of inadvertent stowage of the thrust 
reversers, which can result in high forward engine thrust even though 
the throttle is commanding reverse thrust. These reports were on 
another type of airplane that utilizes a similar engine and thrust 
reverser system. The root cause is incorrect software logic within the 
engine's electronic control unit. This condition, if not corrected, 
could result in inadvertent stowage of the thrust reversers, which 
could cause a runway overrun during a rejected takeoff or during 
landing, and consequent structural failure and possible injury to 
occupants.

Related Service Information Under 1 CFR Part 51

    We reviewed Beechcraft Mandatory Service Bulletin 78-4133, dated 
May 2015. The service information describes procedures for installing 
kits having part numbers 140-9005 and 140-9006, which include relays, 
associated wiring, and a thrust reverser fail annunciator. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''

Differences Between This Proposed AD and the Service Information

    Although Beechcraft Mandatory Service Bulletin 78-4133, dated May 
2015, specifies that ``Should any difficulty be encountered in 
accomplishing this Service Bulletin, contact Beechcraft Corporation,'' 
this proposed AD would require operators to resolve difficulties in 
accordance with a method approved by the FAA.

Costs of Compliance

    We estimate that this proposed AD affects 38 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Installation........................  340 work-hours x $85           $100,000         $128,900       $4,898,200
                                       per hour = $28,900.
----------------------------------------------------------------------------------------------------------------

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

[[Page 3350]]

proposed AD would not have a substantial direct effect on the States, 
on the relationship between the national Government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Beechcraft Corporation (Type Certificate Previously Held by Hawker 
Beechcraft Corporation; Raytheon Aircraft Company): Docket No. FAA-
2016-0460; Directorate Identifier 2015-NM-078-AD.

(a) Comments Due Date

    We must receive comments by March 7, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Beechcraft Corporation (type certificate 
previously held by Hawker Beechcraft Corporation; Raytheon Aircraft 
Company) airplanes, certificated in any category, as identified in 
paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model BAe.125 series 1000A and 1000B airplanes, serial 
numbers 258151, 258159, and 259004 through 259042 inclusive.
    (2) Model Hawker 1000 airplanes, serial numbers 259003 and 
259043 through 259052 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Exhaust.

(e) Unsafe Condition

    This AD was prompted by reports of inadvertent stowage of the 
thrust reversers, which can result in high forward engine thrust 
even though the throttle is commanding reverse thrust. We are 
issuing this AD to prevent inadvertent stowage of the thrust 
reversers, which could cause a runway overrun during a rejected 
takeoff or landing, and consequent structural failure and possible 
injury to occupants.

(f) Compliance

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

(g) Installation

    Within 600 flight hours or 12 months after the effective date of 
this AD, whichever occurs first: Install kits having part numbers 
140-9005 and 140-9006, in accordance with the Accomplishment 
Instructions of Beechcraft Mandatory Service Bulletin 78-4133, dated 
May 2015, except as specified in paragraph (h) of this AD.

(h) Exception to Service Information

    A note in the Accomplishment Instructions of Beechcraft 
Mandatory Service Bulletin 78-4133, dated May 2015, instructs 
operators to contact Beechcraft Corporation if any difficulty is 
encountered in accomplishing the service bulletin. However, any 
deviation from the actions required by paragraph (g) of this AD must 
be approved as an alternative method of compliance (AMOC) under 
paragraph (i)(1) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita 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 (j)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    (1) For more information about this AD, contact Jeffrey Englert, 
Aerospace Engineer, Mechanical Systems and Propulsion Branch, ACE-
116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, 
Room 100, Dwight D. Eisenhower National Airport, Wichita, KS 67209; 
phone: 316-946-4167; fax: 316-946-4107; email: 
jeffrey.englert@faa.gov.
    (2) For service information identified in this AD, contact 
Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201-0085; 
telephone 316-676-8238; fax 316-671-2540; email tmdc@beechcraft.com; 
Internet http://pubs.beechcraft.com. You may view this referenced 
service information at 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 January 8, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00951 Filed 1-20-16; 8:45 am]
BILLING CODE 4910-13-P