Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 42007 

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, 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. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0191, dated 

August 29, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0086-0003. 

(j) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A310–71–2038, 

including Appendices 01 and 02, dated April 

8, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.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, on July 2, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–17202 Filed 7–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23706; Directorate 

Identifier 2006–NE–03–AD; Amendment 39– 

18177; AD 2015–12–04] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to all Honeywell 

International Inc. TPE331–1, –2, –2UA, 

–3U, –3UW, –5, –5A, –5AB, –5B, –6, 

–6A, –10, –10AV, –10GP, –10GT, –10P, 

–10R, –10T, –10U, –10UA, –10UF, 

–10UG, –10UGR, –10UR, –11U, –12JR, 

–12UA, –12UAR, and –12UHR 

turboprop engines with certain 

Honeywell part numbers (P/Ns) of 

Woodward fuel control unit (FCU) 

assemblies, installed. The AD number in 

the document headings is incorrect. 

Additionally, the Amendment number 

in the regulatory text is incorrect. This 

document corrects these two errors. In 

all other respects, the original document 

remains the same. 

DATES: This final rule is effective on July 

22, 2015. The effective date of AD 2015– 

12–04, Amendment 39–18177 (80 FR 

34534, June 17, 2015) remains July 22, 

2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov; 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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210; email: joseph.costa@

faa.gov. 

SUPPLEMENTARY INFORMATION: AD 2015– 

12–04, Amendment 39–18177, 80 FR 

34534, June 17, 2015), requires initial 

and repetitive dimensional inspections 

of the affected fuel control drives and 

insertion of certain airplane operating 

procedures into the applicable flight 

manuals. 

As published, the AD number in the 

document headings is incorrect. 

Additionally, the Amendment number 

in the regulatory text of AD 2015–12–04 

is incorrect. 

No other part of the final rule has 

been changed. 

The effective date of AD 2015–12–04 

remains July 22, 2015. 

Correction of Non-Regulatory Text 

In the Federal Register of June 17, 

2015, AD 2015–12–04; Amendment 39– 

18177 (80 FR 34534) is corrected as 

follows: 

On page 34534, in the 2nd column, on 

line 6, change ‘‘2014–12–04’’ to ‘‘2015– 

12–04’’. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2006–15–08, Amendment 39–14688 (71 

FR 41121, July 20, 2006), and adding the 

following new AD: 

2015–12–04 Honeywell International Inc.: 

Amendment 39–18177; Docket No. 

FAA–2006–23706; Directorate Identifier 

2006–NE–03–AD. 

(a) Effective Date 

This AD is effective August 20, 2015. 

(b) Affected ADs 

This AD replaces AD 2006–15–08, 

Amendment 39–14688 (71 FR 41121, July 20, 

2006). 

(c) Applicability 

This AD applies to all Honeywell 

International Inc. TPE331–1, –2, –2UA, –3U, 

–3UW, –5, –5A, –5AB, –5B, –6, –6A, –10, 

–10AV, –10GP, –10GT, –10P, –10R, –10T, 

–10U, –10UA, –10UF, –10UG, –10UGR, 

–10UR, –11U, –12JR, –12UA, –12UAR, and 

–12UHR turboprop engines with Honeywell 

part numbers (P/Ns) for Woodward fuel 

control unit (FCU) assemblies listed in Table 

1 to paragraph (c) of this AD, installed. 

TABLE 1 TO PARAGRAPH (C)—AFFECTED FCU ASSEMBLY P/NS

Group No. Engine FCU Assembly P/Ns 

1 ..................... TPE331–1, –2, and –2UA ........................ P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33, 

–34, and –35. 


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42008 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (C)—AFFECTED FCU ASSEMBLY P/NS—Continued 

Group No. Engine FCU Assembly P/Ns 

2 * ................... TPE331–1, –2, and –2UA ........................ P/N 869199–9, –10, –11, –12, –14, –16, –17, and –18. 

3 ..................... TPE331–3U, –3UW, –5, –5A, –5AB, –5B, 

–6, –6A, –10AV, –10GP, –10GT, –10P, 

and –10T.

P/N 893561–7, –8, –9, –10, –11, –14, –15, –16, –20, –26, –27, and –29; or 

P/N 897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28. 

4 * ................... TPE331–3U, –3UW, –5, –5B, –6, –6A, 

and –10T.

P/N 893561–4, –5, –12, and –13 or P/N 897770–5, –8, and –13. 

5 ..................... TPE331–10, –10R, –10U, –10UA, 

–10UF, –10UG, –10UGR, –10UR, 

–11U, –12JR, –12UA, –12UAR, and 

–12UHR.

P/N 897375–2, –3, –4, –5, –8, –9, –10, –11, –12, –13, –14, –15, –16, –17, –19, 

–21, –24, –25, –26, and –27; or 

P/N 897780–1, –2, –3, –4, –5, –6, –7, –8, –9, –10, –11, –14, –15, –16, –17, –18, 

–19, –20, –21, –22, –23, –24, –25, –26, –27, –30, –32, –34, –36, –37, and –38; 

or 

P/N 893561–17, –18, and –19. 

* New/added FCU assembly P/Ns 

(d) Unsafe Condition 

We are issuing this AD to prevent failure 

of the fuel control drive that could result in 

damage to the engine and airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Inspection of Engines With FCU Assembly 

P/Ns in Groups 2 and 4 

For FCU assembly P/Ns in Groups 2 and 

4 listed in Table 1 to paragraph (c) of this AD: 

(i) At the next scheduled inspection of the 

fuel control drive, or within 500 hours-inservice (HIS) after the effective date of this 

AD, whichever occurs first, inspect the fuel 

control drive for wear. 

(ii) Thereafter, re-inspect the fuel control 

drive within every 1,000 HIS since-lastinspection (SLI). 

(2) Inspection of Engines With FCU Assembly 

P/Ns in Groups 1, 3, and 5 

For FCU assembly P/Ns in Groups 1, 3, or 

5 listed in Table 1 to paragraph (c) of this AD: 

(i) If on the effective date of this AD the 

FCU assembly has 950 or more HIS SLI, 

inspect the fuel control drive for wear within 

50 HIS from the effective date of this AD. 

(ii) If on the effective date of this AD the 

FCU assembly has fewer than 950 HIS SLI, 

inspect the fuel control drive for wear before 

reaching 1,000 HIS. 

(iii) Thereafter, re-inspect the fuel control 

drive for wear within every 1,000 HIS SLI. 

(3) Airplane Operating Procedures 

Within 60 days after the effective date of 

this AD, insert the information in Figure 1 to 

paragraph (e) of this AD, into the Emergency 

Procedures Section of the Airplane Flight 

Manual (AFM), Pilot Operating Handbook 

(POH), and the Manufacturer’s Operating 

Manual (MOM). 


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Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 42009 

(f) Optional Terminating Action 

Replacing the affected FCU assembly with 

an FAA-approved FCU assembly P/N not 

listed in this AD is terminating action for the 

initial and repetitive inspections required by 

this AD, and for inserting the information in 

Figure 1 to paragraph (e) of this AD into the 

AFM, POH, and MOM. 

(g) Definitions 

For the purposes of this AD: 

(1) The ‘‘fuel control drive’’ is a series of 

mating splines located between the fuel 

pump and fuel control governor. 

(2) The fuel control drive consists of four 

drive splines: the fuel pump internal spline, 

the fuel control external ‘‘quill shaft’’ spline, 

and the stub shaft internal and external 

splines. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210; email: joseph.costa@faa.gov. 

(2) Information pertaining to operating 

recommendations for affected engines after a 

fuel control drive failure is contained in 

Honeywell International Inc., Operating 

Information Letter (OIL) OI331–12R6, dated 

May 26, 2009, for multi-engine airplanes; and 

in OIL OI331–18R4, dated May 26, 2009, for 

single-engine airplanes. Information on fuel 

control drive inspection can be found in 

Section 72–00–00 of the applicable TPE331 

maintenance manuals. These Honeywell 

International Inc., OILs and the TPE331 

maintenance manuals, which are not 

incorporated by reference in this AD, can be 

obtained from Honeywell International Inc., 

using the contact information in paragraph 

(i)(3) of this AD. 

(3) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802; Internet: https://

myaerospace.honeywell.com/wps/portal/!ut; 

phone: 800–601–3099. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(j) Material Incorporated by Reference 

None. 


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42010 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 

Issued in Burlington, Massachusetts, on 

June 26, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine and 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–16587 Filed 7–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1123; Directorate 

Identifier 2014–CE–037–AD; Amendment 

[39–18209; AD 2015–06–02 R1] 

RIN 2120–AA64 

Airworthiness Directives; GA 8 Airvan 

(Pty) Ltd Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an 

airworthiness directive (AD) 2015–06– 

02 for GA 8 Airvan (Pty) Ltd Model 

GA8–TC320 airplanes. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as missing required engine 

mount fire seal washers, which could 

reduce the engine retention capability in 

the event of a fire. We are issuing this 

AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective August 20, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of April 24, 2015 (80 FR 

14810, March 20, 2015). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

1123; or in person at the 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 service information identified in 

this AD, contact GA 8 Airvan (Pty) Ltd, 

c/o GippsAero Pty Ltd, Attn: Technical 

Services, P.O. Box 881, Morwell 

Victoria 3840, Australia; telephone: + 61 

03 5172 1200; fax: +61 03 5172 1201; 

email: techpubs@gippsaero.com; 

Internet: http://www.gippsaero.com/

customer-support/technicalpublications.aspx. 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–2014–1123. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to GA 8 Airvan (Pty) Ltd Model GA8– 

TC320 airplanes. The NPRM was 

published in the Federal Register on 

April 17, 2015 (74 FR 21193), and 

proposed to revise AD 2015–06–02, 

Amendment 39–18120 (80 FR 14810; 

March 20, 2015). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products and was based on mandatory 

continuing airworthiness information 

originated by an airworthiness authority 

of another country. The MCAI states 

that: 

A recent review of the engine mount 

installation on the GA8–TC 320 aircraft has 

highlighted the omission of engine mount 

fire seal washers during the assembly 

process. 

The current engine mount configuration 

does not meet the certification basis for the 

aircraft, specifically regulation 23.865 of the 

Federal Aviation Regulations of the United 

States of America, where engine mounts 

located in designated fire zones are required 

to be suitably shielded so that they are 

capable of withstanding the effects of a fire. 

The Gippsland Aeronautics GA8–TC 320 

aircraft require the installation of an 

approved steel washer at each of the engine 

mount locations to address a potential risk of 

reduced engine retention capability in the 

event of a fire. 

This AD, AD/GA8/8 Amdt 1, amends the 

applicability statement to be inclusive of the 

affected aircraft serial number range. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-1123- 

0007. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (74 

FR 21193, April 17, 2015) 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 the 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 (74 FR 

21193, April 17, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (74 FR 21193, 

April 17, 2015). 

Relative Service Information Under 1 

CFR Part 51 

We reviewed GippsAero Mandatory 

Service Bulletin SB–GA8–2014–115, 

Issue 1, dated October 6, 2014. The 

service bulletin describes procedures for 

inspecting the orientation of the engine 

isolator mounts to verify proper 

installation, re-installing if necessary, 

and installing steel washers on the 

forward side of each side of the engine 

isolator mounts. 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 of this AD. 

Costs of Compliance 

We estimate that this AD will affect 

13 products of U.S. registry. We also 

estimate that it would take about 5 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $10 per 

product. 

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 


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