Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26103 

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 

(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): 

2016–09–04 Bombardier, Inc.: Amendment 

39–18502; Docket No. FAA–2015–4814; 

Directorate Identifier 2015–NM–105–AD. 

(a) Effective Date 

This AD is effective June 6, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, certificated in any category, serial 

numbers 7003 through 7067 inclusive, 7069 

through 7990 inclusive, and 8000 through 

8999 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by the discovery of 

a number of incorrectly calibrated angle of 

attack (AOA) transducers installed in the 

stall protection system. We are issuing this 

AD to detect and replace incorrectly 

calibrated AOA transducers; incorrect 

calibration of the transducers could result in 

late activation of the stick pusher. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

For AOA transducers identified in 

paragraph 1.A., ‘‘Effectivity,’’ of Bombardier 

Service Bulletin 601R–27–164, dated March 

30, 2015: Within 2,500 flight hours or 12 

months, whichever occurs first after the 

effective date of this AD, replace the AOA 

transducers with correctly calibrated AOA 

transducers, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–27–164, dated March 

30, 2015. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, on any airplane, an AOA 

transducer having a part number or serial 

number listed in paragraph 1.A., 

‘‘Effectivity,’’ of Bombardier Service Bulletin 

601R–27–164, dated March 30, 2015. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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: 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, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(j) Related Information 

For more information about this AD, 

contact Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems Branch, 

ANE–171, FAA, New York ACO, 1600 

Stewart Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7318; fax 516– 

794–5531. 

(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) Bombardier Service Bulletin 601R–27– 

164, dated March 30, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(4) You may view this 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. 

(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, on April 20, 

2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–09791 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3970; Directorate 

Identifier 2015–SW–006–AD; Amendment 

39–18497; AD 2016–08–20] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2014–12– 

51 for Airbus Helicopters (previously 

Eurocopter France) Model EC130B4 and 

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26104 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

EC130T2 helicopters. AD 2014–12–51 

required repetitively inspecting the 

tailboom to Fenestron junction frame 

(junction frame) for a crack. This new 

AD retains the requirements of AD 

2014–12–51, changes the applicability 

from helicopters with certain hours 

time-in-service (TIS) to junction frames 

with certain hours TIS, and adds a 

compliance time for sling cycles to the 

junction frame inspection interval. The 

actions of this AD are intended to detect 

a crack and to prevent failure of the 

junction frame, which could result in 

loss of the Fenestron and subsequent 

loss of control of the helicopter. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of June 6, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. It is also on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–3970. 

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–2015– 

3970; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy, Fort Worth, TX 76177; 

email robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 25, 2015, at 80 FR 

57742, the Federal Register published 

our notice of proposed rulemaking 

(NPRM) to amend 14 CFR part 39 to 

remove AD 2014–12–51, Amendment 

39–17921 (79 FR 45335, August 5, 

2014), and add a new AD. AD 2014–12– 

51 applied to Airbus Helicopters Model 

EC130B4 and EC130T2 helicopters with 

690 or more hours TIS and required, 

within 10 hours TIS, dye-penetrant 

inspecting certain areas of the junction 

frame for a crack. AD 2014–12–51 also 

required, at intervals not exceeding 25 

hours TIS, either repeating the dyepenetrant inspection or performing a 

borescope inspection of certain areas of 

the junction frame for a crack. If there 

was a crack, AD 2014–12–51 required 

replacing the junction frame. AD 2014– 

12–51 was prompted by two incidents 

of crack propagation through the 

junction frame that initiated in the 

lower right-hand side between the web 

and the flange where the lower spar of 

the tailboom is joined. The cracks were 

significant in length and not visible 

from the outside of the helicopter. 

The NPRM was prompted by AD No. 

2015–0033–E dated February 24, 2015 

(AD 2015–0033–E), issued by EASA, 

which is the Technical Agent for the 

Member States of the European Union, 

to correct an unsafe condition on Airbus 

Helicopters EC130B4 and EC130T2 

helicopters. The NPRM proposed to 

require retaining the dye penetrant and 

borescope inspections in AD 2014–12– 

51 but with revised compliance times. 

The NRPM also proposed to change the 

applicability to helicopters with 690 

hours TIS accumulated on the junction 

frame instead of on the helicopter, and 

proposed including an inspection 

interval defined in sling cycles. These 

actions were intended to detect a crack 

and to prevent failure of the junction 

frame, which could result in loss of the 

Fenestron and subsequent loss of 

control of the helicopter. 

Comments 

After our NPRM (80 FR 57742, 

September 25, 2015) was published, we 

received a comment from one 

commenter. 

Request 

One commenter requested the 

addition of a 10-hour or 250-sling cycle 

visual pilot check for helicopters with 

Modification 350A087421 or that have 

complied with Airbus Helicopters 

Service Bulletin No. EC130–53–029, 

Revision 0, dated February 20, 2015 (SB 

EC130–53–029). The commenter stated 

this pilot check would benefit operators 

and provide the same level of safety. 

We disagree. While the EASA AD 

allows the check requested by the 

commenter as an alternative method, 

because the cause of the fatigue cracking 

is still under investigation, we cannot 

determine that this method would 

correct the unsafe condition. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA, reviewed the 

relevant information, considered the 

comment received, and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking 

then. 

Differences Between This AD and the 

EASA AD 

The EASA AD includes alternate 

compliance instructions for helicopters 

modified with a cut-out in production 

by Airbus Helicopters Modification 

350A087421 or in service by 

compliance with SB EC130–53–029. 

This AD does not. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Helicopters 

Emergency Alert Service Bulletin No. 

05A017, Revision 2, dated February 20, 

2015 (EASB 05A017), for Model 

EC130B4 and EC130T2 helicopters. 

EASB 05A017 describes alternate 

procedures for inspecting outside the 

tailboom for a crack at reduced 

inspection intervals in combination 

with the internal inspections at 

extended intervals. EASB 05A017 also 

specifies adding sling cycles to the 

existing flight hour inspection interval 

for helicopters that perform external 

load-carrying operations. EASA issued 

AD No. 2015–0033–E mandating the 

requirements in EASB 05A017 to ensure 

the continued airworthiness of these 

helicopters. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26105 

course of business or by the means 

identified in the ADDRESSES section. 

Other Related Service Information 

Airbus Helicopters also issued SB 

EC130–53–029, which contains 

procedures to cut out the skin and 

splice at the junction frame to facilitate 

the external inspection specified in 

EASB 05A017. 

Costs of Compliance 

We estimate that this AD affects 208 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

At an average labor rate of $85 per workhour, dye-penetrant inspecting the 

junction frame will require 1 work-hour, 

for a cost of $85 per helicopter and a 

total cost of $17,680 for the U.S. fleet, 

per inspection cycle. Borescope 

inspecting the junction frame will 

require 0.5 work-hour, for a cost of $43 

per helicopter and a total cost of $8,944 

for the U.S. fleet, per inspection cycle. 

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 

helicopters 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 

removing Airworthiness Directive (AD) 

2014–12–51, Amendment 39–17921 (79 

FR 45335, August 5, 2014), and adding 

the following new AD: 

2016–08–20 Airbus Helicopters (Previously 

Eurocopter France): Amendment 39– 

18497; Docket No. FAA–2015–3970; 

Directorate Identifier 2015–SW–006–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model EC130B4 and EC130T2 helicopters 

with a tailboom to fenestron junction frame 

(junction frame) that has 690 or more hours 

time-in-service (TIS), certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the junction frame. This condition 

could result in failure of the junction frame, 

which could result in loss of the Fenestron 

and subsequent loss of control of the 

helicopter. 

(c) Affected ADs 

This AD supersedes AD 2014–12–51, 

Amendment 39–17921 (79 FR 45335, August 

5, 2014). 

(d) Effective Date 

This AD becomes effective June 6, 2016. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Before the junction frame reaches 700 

hours TIS or within 10 hours TIS, whichever 

occurs later, remove the horizontal stabilizer, 

clean the junction frame, and dye-penetrant 

inspect around the circumference of the 

junction frame for a crack in the areas shown 

in Figure 1 of Airbus Helicopters EC130 

Emergency Alert Service Bulletin No. 

05A017, Revision 2, dated February 20, 2015 

(EASB 05A017). Pay particular attention to 

the area around the 4 spars (item b) of Figure 

1 of EASB 05A017. An example of a crack 

is shown in Figure 3 of EASB 05A017. 

(2) Within 25 hours TIS or 390 sling cycles, 

whichever occurs first after the inspection 

required by paragraph (f)(1) of this AD, and 

thereafter at intervals not exceeding 25 hours 

TIS or 390 sling cycles, whichever occurs 

first, either perform the actions of paragraph 

(f)(1) of this AD or, if the area is clean, using 

a borescope, inspect around the 

circumference of the junction frame for a 

crack in the areas shown in Figure 2 of EASB 

05A017. Pay particular attention to the area 

around the 4 spars (item b) of Figure 2 of 

EASB 05A017. An example of a crack is 

shown in Figure 3 of EASB 05A017. For 

purposes of this AD, a sling cycle is defined 

as one landing with or without stopping the 

rotor or one external load-carrying operation; 

an external load-carrying operation occurs 

each time a helicopter picks up an external 

load and drops it off. 

(3) If there is a crack, before further flight, 

replace the junction frame. 

(g) Special Flight Permits 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

(1) Airbus Helicopters Service Bulletin No. 

EC130–53–029, Revision 0, dated February 

20, 2015, which is not incorporated by 

reference, contains additional information 

about the subject of this final rule. For 

service information identified in this final 

rule, contact Airbus Helicopters, Inc., 2701 

N. Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 

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26106 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2015–0033–E, dated February 24, 2015. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2015–3970. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302: Rotorcraft Tailboom. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Emergency Alert 

Service Bulletin No. 05A017, Revision 2, 

dated February 20, 2015. 

(ii) Reserved. 

(3) For Airbus Helicopters service 

information identified in this final rule, 

contact Airbus Helicopters, Inc., 2701 N. 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on April 15, 

2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–09235 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0338; Directorate 

Identifier 2014–CE–010–AD; Amendment 

39–18495; AD 2016–08–18] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Piper Aircraft, Inc. Model PA–31–350 

airplanes. This AD was prompted by a 

report of an engine fire caused by a leak 

in the fuel pump inlet hose. This AD 

requires inspecting the fuel hose 

assembly and the turbocharger support 

assembly for proper clearance between 

them, inspecting each assembly for any 

sign of damage, and making any 

necessary repairs or replacements. We 

are issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 6, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Piper Aircraft, Inc., 2926 Piper Drive, 

Vero Beach, Florida 32960; telephone: 

(772) 567–4361; fax: (772) 978–6573; 

Internet: www.piper.com/home/pages/

Publications.cfm. You may view this 

referenced service information at the 

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. It is also available on the internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0338. 

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–2014– 

0338; 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 

Document 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: Gary 

Wechsler, Aerospace Engineer, FAA, 

Atlanta Aircraft Certification Office, 

1701 Columbia Avenue, College Park, 

Georgia 30337; telephone: (404) 474– 

5575; fax: (404) 474–5606; email: 

gary.wechsler@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to certain Piper 

Aircraft, Inc. Model PA–31–350 

airplanes. The SNPRM published in the 

Federal Register on January 26, 2016 

(81 FR 4214). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on June 3, 2014 (79 FR 31888). 

The NPRM proposed to require 

inspecting the fuel hose assembly and 

the turbocharger support assembly for 

proper clearance between them, 

inspecting each assembly for any sign of 

damage, and making any necessary 

repairs or replacements. The NPRM was 

prompted by a report of an engine fire 

on a Piper Aircraft, Inc. (Piper) Model 

PA–31–350 airplane. Investigation 

revealed that the fire was caused by a 

leak in the fuel pump inlet hose that 

resulted from repeated contact with an 

adjacent turbocharger support assembly 

caused by inadequate clearance between 

the two assemblies. The SNPRM 

proposed to require the same actions as 

proposed in the NPRM using revised 

service information issued by the 

manufacturer to clarify which engines 

are part of the airplane applicability and 

to revise the instructions for 

accomplishing the proposed actions. 

This condition, if not corrected, could 

result in damage to the fuel inlet hose 

assembly, which could cause the fuel 

pump inlet hose to fail and leak fuel in 

the engine compartment. This condition 

could also cause damage to the 

turbocharger support assembly, which 

could require the turbocharger support 

assembly to be repaired or replaced. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(81 FR 4214, January 26, 2016) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data 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 SNPRM (81 FR 

4214, January 26, 2016) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (81 FR 4214, 

January 26, 2016). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Piper Aircraft, Inc. 

Service Bulletin No. 1257A, dated 

August 4, 2015. The service information 

describes procedures for the following. 

This service information is reasonably 

mstockstill on DSK3G9T082PROD with RULES