44494 Federal Register / Vol. 81, No. 131 / Friday, July 8, 2016 / Rules and Regulations 

replace with bolts, P/N NAS 6203–6X or –7X, 

as indicated for the position, assembled with 

washers, P/N AN960–10, and nut, P/N 

MS21044N3, at the compliance time 

specified in paragraphs (f)(2)(i) and (ii) of this 

AD. 

(i) For airplanes previously affected by AD 

2006–13–05: Within the next 100 hours timein-service (TIS) after July 31, 2006 (the 

effective date retained from AD 2006–13–05). 

Do the removal and replacement actions 

following Pacific Aerospace Corporation Ltd. 

Service Bulletin PACSB/XL/018, Issue 3, 

dated December 23, 2005, and amended 

January 16, 2006. 

(ii) For airplanes new to this AD: Within 

the next 100 hours TIS after August 12, 2016 

(the effective date of this AD) or within the 

next 12 months after August 12, 2016 (the 

effective date of this AD), whichever occurs 

first. Do the removal and replacement actions 

following Pacific Aerospace Limited Service 

Bulletin PACSB/XL/018, Issue 4, dated 

January 20, 2016. 

(3) For all affected airplanes: Before further 

flight after doing the action required in 

paragraph (f)(2) of this AD, remove the 

restrictive information from the Limitations 

section of the AFM that you were required 

to insert in paragraph (f)(1) of this AD. The 

owner/operator holding at least a private 

pilot certificate as authorized by section 43.7 

of the Federal Aviation Regulations (14 CFR 

43.7) may do the flight manual changes 

requirement of this AD. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI Civil Aviation Authority 

(CAA) AD No. DCA/750XL/7B, dated 

February 25, 2016, for related information. 

You may examine the MCAI on the Internet 

at https://www.regulations.gov/

#!docketDetail;D=FAA-2016-5578-002. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on August 12, 2016. 

(i) Pacific Aerospace Limited Service 

Bulletin PACSB/XL/018, Issue 4, dated 

January 20, 2016. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on July 31, 2006 (71 FR 

35509, June 21, 2006). 

(i) Pacific Aerospace Corporation Ltd. 

Service Bulletin PACSB/XL/018, Issue 3, 

dated December 23, 2005, and amended 

January 16, 2006. 

(ii) Reserved. 

(5) For Pacific Aerospace Limited service 

information identified in this AD, contact 

Pacific Aerospace Limited, Airport Road, 

Hamilton, Private Bag 3027, Hamilton 3240, 

New Zealand; telephone: +64 7 843 6144; 

facsimile: +64 7 843 6134; email: pacific@

aerospace.co.nz; Internet: 

www.aerospace.co.nz. 

(6) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. In 

addition, you can access this service 

information on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2016–5578. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on June 

28, 2016. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–15864 Filed 7–7–16; 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; Amendment 

39–18577; AD 2016–13–13] 

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: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Beechcraft Corporation Model BAe.125 

Series 1000A and 1000B airplanes and 

Model Hawker 1000 airplanes. 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. This AD requires 

installing kits that include relays, 

associated wiring, and a thrust reverser 

fail annunciator. 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. 

DATES: This AD is effective August 12, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 12, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0460. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Englert, Aerospace Engineer, 

Systems and Propulsion Branch, ACE– 

116W, FAA, Wichita Aircraft 

Certification Office (ACO), 1801 Airport 

Road, Room 100, Dwight D. Eisenhower 


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Federal Register / Vol. 81, No. 131 / Friday, July 8, 2016 / Rules and Regulations 44495 

National Airport, Wichita, KS 67209; 

phone: 316–946–4167; fax: 316–946– 

4107; email: jeffrey.englert@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Beechcraft Corporation 

Model BAe.125 series 1000A and 1000B 

airplanes and Model Hawker 1000 

airplanes. The NPRM published in the 

Federal Register on January 21, 2016 

(81 FR 3348) (‘‘the NPRM’’). The NPRM 

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. The NPRM proposed to 

require installing kits that include 

relays, associated wiring, and a thrust 

reverser fail annunciator. 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

Mr. Kevin Maher expressed support 

for the NPRM. 

Request To Revise NPRM Requirement 

Mr. Kenneth Rittenhouse of Becker 

Aviation LLC requested that we not 

require installation of the service kits, 

but leave the installation decision up to 

the individual owner/operator. Mr. 

Rittenhouse stated that the NPRM 

mentions that there have not been any 

issues reported involving Model 

BAe.125 airplanes but does mention 

that those airplanes have a similar 

engine/thrust reverser system to 

airplanes on which the problem was 

reported. Mr. Rittenhouse explained 

that if you examine the Learjet Model 60 

and the Model Hawker 1000 systems, 

the Hawker 1000 is much more robust 

with redundant capabilities. Mr. 

Rittenhouse stated that he does not 

believe the unsafe condition has ever 

been an issue with the Model Hawker 

1000 airplanes, and that it is extremely 

unjust to force operators to comply with 

this modification that costs 15 percent 

of the total value of the airplane. 

We do not agree with the commenter’s 

request. We recognize that maintaining 

airplanes in an airworthy condition is 

vital, but sometimes expensive. 

Installation of the service kit corrects a 

potential unsafe condition that could 

cause a runway overrun during a 

rejected takeoff or landing, and 

consequent structural failure and 

possible injury to occupants. The 

service kit was designed and proposed 

by the airplane original equipment 

manufacturer as its best correction 

option. The root cause of the unsafe 

condition is incorrect software logic 

within the engine’s electronic control 

unit. We acknowledge the commenter’s 

statement indicating that ‘‘the Hawker 

1000 is much more robust with 

redundant capabilities,’’ however, the 

commenter did not submit any 

substantiating data to support that 

statement. We have determined that this 

unsafe condition exists on the Model 

Hawker 1000 airplanes as well as 

Beechcraft Corporation Model BAe.125 

Series 1000A and 1000B airplanes. We 

might approve requests to revise the 

applicability of this AD if the request 

includes data that justifies such a 

revision and provides an acceptable 

level of safety. We have not changed 

this AD in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Beechcraft 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. 

Costs of Compliance 

We estimate that this AD affects 38 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 


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44496 Federal Register / Vol. 81, No. 131 / Friday, July 8, 2016 / Rules and Regulations 

(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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2016–13–13 Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon 

Aircraft Company): Amendment 39– 

18577; Docket No. FAA–2016–0460; 

Directorate Identifier 2015–NM–078–AD. 

(a) Effective Date 

This AD is effective August 12, 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, Engine 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 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 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 the provisions 

of paragraph (i)(1) of this AD. 

(i) Alternative Methods of Compliance 

(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) 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 

For more information about this AD, 

contact Jeffrey Englert, Aerospace Engineer, 

Systems and Propulsion Branch, ACE–116W, 

FAA, Wichita ACO, 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. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Beechcraft Service Bulletin 78–4133, 

dated May 2015. 

(ii) Reserved. 

(3) For Beechcraft 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, June 22, 

2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–15622 Filed 7–7–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2964; Directorate 

Identifier 2014–NM–206–AD; Amendment 

39–18584; AD 2016–14–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A319, A320, and A321 

series airplanes. This AD is intended to 

complete certain mandated programs 

intended to support the airplane 

reaching its limit of validity (LOV) of 

the engineering data that support the 

established structural maintenance 

program. This AD requires reinforcing 

the forward pressure bulkhead at a 

certain stringer on both the left-hand 

and right-hand sides, and doing related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

prevent fatigue cracking of the forward 

pressure bulkhead, which could result 

in reduced structural integrity of the 

airplane. 

DATES: This AD becomes effective 

August 12, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 12, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus, Airworthiness Office—EIAS, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 


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