36440 Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 

certificated in any category, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by the need for 

more restrictive airworthiness limitations. 

We are issuing this AD to reduce the 

potential for significant failure conditions 

and consequent loss of controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

(1) Within 12 months after the effective 

date of this AD, revise the maintenance or 

inspection program, as applicable, to 

incorporate the certification maintenance 

requirements (CMR) specified in ‘‘Fokker 70/ 

100 Certification Maintenance 

Requirements,’’ of Fokker Services B.V. 

Engineering Report, Airworthiness 

Limitations Section (ALS), SE–473, Issue 11, 

released January 19, 2015. 

(2) Do the applicable initial CMR 

inspection at the time specified in paragraph 

(g)(2)(i) or (g)(2)(ii) of this AD, as applicable, 

as specified in ‘‘Fokker 70/100 Certification 

Maintenance Requirements,’’ of Fokker 

Services B.V. Engineering Report, ALS, SE– 

473, Issue 11, released January 19, 2015. If 

any discrepancy is found during any 

inspection, repair using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency; or 

Fokker B.V. Service’s EASA Design 

Organization Approval (DOA). Repair any 

discrepancy before further flight. 

(i) For CMR inspection 783100–CM–01: 

Within 1 year or 3,000 flight hours after the 

effective date of this AD, whichever occurs 

first, but not later than 12,000 flight hours 

after accomplishing Maintenance Review 

Board (MRB) Task 783100–00–04. 

(ii) For CMR inspection 783500–CM–01: 

Within 1 year or 3,000 flight hours after the 

effective date of this AD, whichever occurs 

first, but not later than 10,000 flight hours 

after accomplishing MRB Task 783100–01– 

01. 

(h) No Alternative Inspections or Inspection 

Intervals 

After accomplishment of the actions 

specified in paragraph (g)(1) of this AD, no 

alternative actions (e.g., inspections) and 

intervals, may be used, unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (i)(1) of this AD. 

(i) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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: 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 EASA; or Fokker Services B.V.’s EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0027, dated 

February 20, 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–2016–0464. 

(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 this AD specifies otherwise. 

(i) Fokker Services B.V. Engineering 

Report, Airworthiness Limitations Section 

(ALS), SE–473, Issue 11, released January 19, 

2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.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 May 26, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–13101 Filed 6–6–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5810; Directorate 

Identifier 2014–NM–116–AD; Amendment 

39–18526; AD 2016–10–15] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by a design review that 

revealed that a wiring failure, external 

to the center wing fuel tank, could cause 

a hot short circuit to a maximum level 

sensor wire, and result in excessive 

heating of the maximum level sensor 

element. This AD requires modifying 

the wiring of the maximum level 

sensors in the center wing fuel tank, 

performing after-installation tests, and 

corrective action if necessary. This AD 

also requires revising the airplane 

maintenance or inspection program to 

incorporate fuel airworthiness 

limitation items and critical design 

configuration control limitations. We 

are issuing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD becomes effective July 

12, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 12, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 1357, 2130 EL 

Hoofddorp, the Netherlands; telephone 

+31 (0)88–6280–350; fax +31 (0)88– 

6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. You may view 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 36441 

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–2015– 

5810. 

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– 

5810; 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 regulation 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

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 Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 

airplanes. The NPRM published in the 

Federal Register on November 27, 2015 

(80 FR 74039) (‘‘the NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0138, dated May 30, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Fokker 

Services B.V. Model F.28 Mark 0070 

and 0100 airplanes. The MCAI states: 

* * * [T]he FAA published Special Federal 

Aviation Regulation (SFAR) 88, and the Joint 

Aviation Authorities (JAA) published Interim 

Policy INT/POL/25/12. 

The review conducted by Fokker Services 

on the Fokker 70/100 design, in response to 

these regulations, revealed that a wiring 

failure, external to the centre wing fuel tank, 

causing a hot short circuit to a maximum 

(max) level sensor wire may result in 

excessive heating of the max level sensor 

element. 

This condition, if not corrected, could 

create an ignition source in the centre wing 

fuel tank vapour space, possibly resulting in 

a fuel tank explosion and consequent loss of 

the aeroplane. 

EASA issued AD 2012–0240 [http://

ad.easa.europa.eu/blob/easa_ad_2012_

0240.pdf/AD_2012-0240], to address this 

unsafe condition, which required installation 

of three fuses in the wiring of the max level 

sensor(s) in the centre wing fuel tank per 

Fokker Services Service Bulletin (SB) 

SBF100–28–073. After that AD was issued, it 

was found that this technical solution caused 

fuel spills during refueling and, 

consequently, EASA cancelled AD 2012– 

0240. 

More recently, Fokker Services issued 

SBF100–28–078, which cancelled SBF100– 

28–073, to correct the unsafe condition 

without the risk of fuel spills. 

For the reasons described above, this 

[EASA] AD requires removal of one fuse from 

post-SBF100–28–073 aeroplanes, and 

installation of only two fuses on pre-SBF100– 

28–073 aeroplanes and, subsequently, the 

implementation of the associated Critical 

Design Configuration Control Limitation 

(CDCCL) items. 

More information this subject can be found 

in Fokker Services All Operators Message 

AOF100.186#03. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5810. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Changes Made to This 

AD 

We have made the following changes 

to this AD. These changes are for 

formatting purposes and do not affect 

the requirements of this AD. 

• Added a new paragraph (j) to this 

AD to specify the required service 

information, and redesignated 

subsequent paragraphs accordingly. 

• Revised paragraph (g) of this AD by 

referring to the document citations in 

paragraph (j) of this AD. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and 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 Fokker Service Bulletin 

SBF100–28–078, dated January 23, 

2014, and Fokker Manual Change 

Notification MCNM–F100–166, dated 

January 23, 2014. 

This service information describes 

procedures for modifying the wiring of 

the maximum level sensors in the center 

wing fuel tank, after-installation tests, 

and corrective action if necessary. 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 15 

airplanes of U.S. registry. 

We also estimate that it takes up to 9 

work-hours per product to modify the 

wiring of the maximum level sensors in 

the center wing fuel tank, as specified 

in this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $1,700 per product. Based on 

these figures, we estimate the cost of 

this modification on U.S. operators to be 

up to $36,975, or up to $2,465 per 

product. 

We also estimate that it takes about 1 

work-hour per product to revise the 

maintenance or inspection program as 

specified in this AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this revision on U.S. operators to be 

$1,275, or $85 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 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 


jstallworth on DSK7TPTVN1PROD with RULES
36442 Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 

Regulatory Findings 

We determined that 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 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. 

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): 

2016–10–15 Fokker Services B.V.: 

Amendment 39–18526. Docket No. 

FAA–2015–5810; Directorate Identifier 

2014–NM–116–AD. 

(a) Effective Date 

This AD becomes effective July 12, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, 

certificated in any category, equipped with a 

center wing tank. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a design review 

which revealed that a wiring failure, external 

to the center wing fuel tank, could cause a 

hot short circuit to a maximum level sensor 

wire, and result in excessive heating of the 

maximum level sensor element. We are 

issuing this AD to prevent the potential of 

ignition sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Wiring Modification 

Within 24 months after the effective date 

of this AD: Modify the wiring of the 

maximum level sensors of the center wing 

fuel tank, as specified in paragraph (g)(1) or 

(g)(2) of this AD, as applicable. Before further 

flight after accomplishing the modification, 

do all applicable tests and corrective actions, 

in accordance with Part 5 of the 

Accomplishment Instructions of the service 

information identified in paragraph (j) of this 

AD. 

(1) For post-SBF100–28–073 configuration 

airplanes: Do the modification in accordance 

with Part 1 or Part 3, as applicable, of the 

Accomplishment Instructions of the service 

information identified in paragraph (j) of this 

AD. 

(2) For pre-SBF100–28–073 configuration 

airplanes: Do the modification in accordance 

with Part 2 or Part 4, as applicable, of the 

Accomplishment Instructions of the service 

information identified in paragraph (j) of this 

AD. 

(h) Revise the Maintenance or Inspection 

Program 

Within 30 days after installing the 

modification specified in paragraph (g)(1) or 

(g)(2) of this AD, as applicable: Revise the 

airplane maintenance or inspection program, 

as applicable, to incorporate the fuel 

airworthiness limitation items and critical 

design configuration control limitations 

(CDCCLs) specified in paragraph 2.L.(1)(c) of 

Fokker Service Bulletin SBF100–28–078, 

dated January 23, 2014. 

(i) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections), intervals, or 

CDCCLs may be used unless the actions, 

intervals, or CDCCLs are approved as an 

alternative method of compliance in 

accordance with the procedures specified in 

paragraph (k)(1) of this AD. 

(j) Required Service Information 

Do the actions specified in this AD in 

accordance with Fokker Service Bulletin 

SBF100–28–078, dated January 23, 2014, and 

Fokker Manual Change Notification MCNM– 

F100–166, dated January 23, 2014, as 

applicable. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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. 

(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 Fokker B.V. Service’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0138, dated 

May 30, 2014, 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– 

2015–5810. 

(m) 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) Fokker Service Bulletin SBF100–28– 

078, dated January 23, 2014, including the 

attached required drawings specified in 

paragraphs (m)(2)(i)(A), (m)(2)(i)(B), and 

(m)(2)(i)(C) of this AD, as applicable. 

(A) Drawing W41192, Sheet 052, Issue AW, 

‘‘Retro-Fit Wiring Diagram, Tank Fueling/

Defueling, Center Tank,’’ undated; 

(B) Drawing W41192, Sheet 054, Issue AW, 

‘‘Retro-Fit Wiring Diagram, Tank Fueling/

Defueling,’’ undated; and 

(C) Drawing W59520–405, ‘‘Cableloom 

Connection List,’’ Sheet 3, Issue F, dated May 

12, 2011. 

(ii) Fokker Manual Change Notification 

MCNM–F100–166, dated January 23, 2014. 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 36443 

(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 May 12, 

2016. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–11928 Filed 6–6–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7533; Directorate 

Identifier 2015–NM–080–AD; Amendment 

39–18528; AD 2016–11–01] 

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 certain 

Airbus Model A330–200 and –300 series 

airplanes, Model A330–200 Freighter 

series airplanes, and Model A340–541 

and A340–642 airplanes. This AD was 

prompted by a report of an undertorqued forward engine mount bolt. 

This AD requires a one-time torque 

check of the forward and aft engine 

mount bolts and corrective actions if 

necessary. We are issuing this AD to 

detect and correct improperly torqued 

engine mount bolts, which could lead to 

detachment of the engine from the 

airplane during flight and consequent 

damage to the airplane and injury to 

persons on the ground. 

DATES: This AD is effective July 12, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 12, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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 

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–2015–7533. 

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– 

7533; 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 street address for 

the Docket Office (telephone 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: 

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. 

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 Airbus Model A330– 

200 and –300 series airplanes, Model 

A330–200 Freighter series airplanes, 

and Model A340–541 and A340–642 

airplanes. The NPRM published in the 

Federal Register on December 29, 2015 

(80 FR 81216) (‘‘the NPRM’’). The 

NPRM was prompted by a report of an 

under-torqued forward engine mount 

bolt. The NPRM proposed to require a 

one-time torque check of the forward 

and aft engine mount bolts, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

improperly torqued engine mount bolts, 

which could lead to detachment of the 

engine from the airplane during flight 

and consequent damage to the airplane 

and injury to persons on the ground. 

The European Aviation Safety 

Agency, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0082, dated May 11, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on certain Airbus 

Model A330–200 and –300 series 

airplanes, Model A330–200 Freighter 

series airplanes, and Model A340–541 

and A340–642 airplanes. The MCAI 

states: 

In 2013, during a pre-delivery test on an 

A330 aeroplane fitted with Pratt & Whitney 

(PW) PW4170 engines, an issue with N1 [low 

pressure spool] vibrations level on [engine] 

ENG1 was identified. While performing an 

engine removal, one forward engine mount 

bolt was found improperly torqued. The 

investigation concluded this was due to a 

production line engine installation quality 

issue. Further analysis showed that some 

aeroplanes, delivered between June 2006 and 

January 2014, may have had the rear (AFT) 

and forward (FWD) engine mount bolts 

improperly torqued. 

This condition, if not detected and 

corrected, could ultimately lead to an inflight detachment of the engine from the 

aeroplane, possibly resulting in damage to 

the aeroplane and/or injury to persons on the 

ground. 

Prompted by these findings, Airbus issued 

four Alert Operators Transmissions (AOT) 

A71L004–14 (for A330 aeroplanes fitted PW 

engines), AOT A71L006–14 (for A330 

aeroplanes fitted with General Electric (GE) 

engines), AOT A71L005–14 (for A330 

aeroplanes fitted with Rolls Royce (RR) Trent 

700 engines) and AOT A71L008–14 (for A340 

aeroplanes fitted with RR Trent 500 engines) 

to provide torque check instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time torque check 

of the FWD and AFT engine mount bolts and, 

depending on findings, re-torque of the 

affected [engine mount] bolt(s) and/or 

replacement of all four [engine mount] bolts 

and associated nuts. 

Findings (or discrepancies) include 

one engine mount bolt that is loose or 

able to rotate, two or more engine mount 

bolts that are loose or able to rotate, or 

one or more engine mount bolts that are 

fully broken. Corrective actions include 

re-torqueing the affected engine mount 

bolt(s), and replacing all engine mount 

bolts and associated nuts with new 

engine mount bolts and nuts on the 

engine where the loose or fully broken 

engine mount bolt(s) were detected. 

This AD specifies reporting of all 

findings (including no discrepancies). 

The corrective actions include retorqueing loose engine mount bolts 

before further flight. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–7533. 


jstallworth on DSK7TPTVN1PROD with RULES