3348 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules 

§ 39.13 [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. 

(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 

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-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 

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 

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 

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 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules 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

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 

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 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
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. 

(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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0457; Directorate 

Identifier 2015–NM–084–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) 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– 


jstallworth on DSK7TPTVN1PROD with PROPOSALS