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
36444 Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 

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. 

Changes to the NPRM 

Paragraphs (h)(1)(ii) and (i) of the 

proposed AD refer to the 

accomplishment of Airbus Service 

Bulletin A330–71–3028, Revision 01, 

dated February 20, 2012. However, 

operators might also accomplish Airbus 

Service Bulletin A330–71–3028, 

Revision 02, dated August 31, 2015. 

Therefore, we have revised paragraphs 

(h)(1)(ii) and (i) of this AD to refer to the 

actions specified in ‘‘Airbus Service 

Bulletin A330–71–3028.’’ 

Paragraph (m)(1) of the proposed AD 

refers to Airbus AOT A71L008–14, 

dated September 29, 2014, and is an 

exception to the service information 

specified in paragraph (l) of the 

proposed AD. However, paragraph (l) of 

the proposed AD refers to Airbus AOT 

A71L008–14, Revision 01, dated 

December 18, 2014. We have revised 

paragraph (m)(1) of this AD to refer to 

Airbus AOT A71L008–14, Revision 01, 

dated December 18, 2014. 

For consistency, we have also 

replaced the words ‘‘bolt(s)’’ and ‘‘pylon 

bolt(s)’’ in this AD with ‘‘engine mount 

bolt(s)’’ in order to match the language 

in the MCAI. In the service information 

referenced in this AD, the term ‘‘pylon’’ 

is also used in some sentences to 

describe the engine mount bolts. 

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 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. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We have reviewed the following 

service information. 

• Airbus AOT A71L004–14, Revision 

01, dated April 7, 2014. The service 

information describes procedures for 

doing a one-time torque check to 

determine if there are any loose or fully 

broken engine mount bolts at four 

positions at the forward engine pylon 1 

and pylon 2 of Airbus Model A330 

series airplanes having PW engines, 

doing corrective actions, and reporting 

all findings. 

• Airbus AOT A71L005–14, Revision 

01, dated December 11, 2014. The 

service information describes 

procedures for doing a one-time torque 

check to determine if there are any loose 

or fully broken engine mount bolts at 

four positions at the forward engine 

pylon 1 and pylon 2 of Airbus Model 

A330 series airplanes having RR Trent 

700 engines, doing corrective actions, 

and reporting all findings. 

• Airbus AOT A71L006–14, dated 

July 22, 2014. The service information 

describes procedures for doing a onetime torque check to determine if there 

are any loose or fully broken engine 

mount bolts at five FWD and four AFT 

positions at the forward engine pylon 1 

and pylon 2 of Airbus Model A330 

series airplanes having GE engines, 

doing corrective actions, and reporting 

all findings. 

• Airbus AOT A71L008–14, Revision 

01, dated December 18, 2014. The 

service information describes 

procedures for doing a one-time torque 

check to determine if there are any loose 

or fully broken engine mount bolts at 

four positions at the forward engine 

pylon 1 and pylon 2 of Airbus Model 

A340 series airplanes having Trent 500 

engines, doing corrective actions, and 

reporting all findings. 

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 55 

airplanes of U.S. registry. 

We also estimate that it will take 

about 12 work-hours per product to 

comply with the basic requirements of 

this AD, and 1 work-hour per product 

to report torque check findings. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$60,755, or $1,105 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 20 work-hours and require parts 

costing $90,200 for a cost of $91,900 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

Office of Management and Budget 

(OMB) control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 


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Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 36445 

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): 

2016–11–01 Airbus: Amendment 39–18528. 

Docket No. FAA–2015–7533; Directorate 

Identifier 2015–NM–080–AD. 

(a) Effective Date 

This AD is effective July 12, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1) through (c)(5) 

of this AD, certificated in any category, from 

manufacturer serial number (MSN) 0715 

through MSN 1507 inclusive, and MSN 1509, 

except airplanes on which all engines have 

been removed and/or replaced since the date 

of the first flight of the airplane. 

(1) Airbus Model A330–201, –202, –203, 

–223, and –243 airplanes. 

(2) Airbus Model A330–223F and –243F 

airplanes. 

(3) Airbus Model A330–301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(4) Airbus Model A340–541 airplanes. 

(5) Airbus Model A340–642 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by a report of an 

under-torqued forward engine mount bolt. 

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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Affected Engine 

For the purpose of this AD, an affected 

engine is an engine that has never been 

removed and/or replaced since first flight of 

the airplane. 

(h) Action for Airbus Model A330 Airplanes 

Equipped With Pratt and Whitney (PW) 

Engines 

(1) For Airbus Model A330–200, –200 

Freighter, and –300 series airplanes equipped 

with PW engines: At the earlier of the times 

specified in paragraph (h)(1)(i) and (h)(1)(ii) 

of this AD, accomplish a one-time torque 

check of the forward (FWD) and rear (AFT) 

engine mount bolts on each affected engine, 

at the locations specified in, and in 

accordance with the instructions of Section 

4.2.2, ‘‘Inspection Requirements,’’ of Airbus 

Alert Operators Transmission (AOT) 

A71L004–14, Revision 01, dated April 7, 

2014. 

(i) Within 2,000 flight hours after the 

effective date of this AD. 

(ii) During the accomplishment of actions 

specified in Airbus Service Bulletin A330– 

71–3028, if done after the effective date of 

this AD. 

(2) If, during the torque check required by 

paragraph (h)(1) of this AD, only one FWD 

engine mount bolt is found that rotates: Do 

the actions specified in paragraph (h)(2)(i), 

(h)(2)(ii), (h)(2)(iii), or (h)(2)(iv) of this AD, as 

applicable. 

(i) For Airbus Model A330–200 and -300 

series airplanes with an average flight time of 

greater than 132 minutes and having 

accumulated less than 2,350 flight cycles and 

less than 24,320 flight hours since first flight 

of the airplane: Before further flight, retorque the affected engine mount bolt, and, 

within 2,350 flight cycles or 24,320 flight 

hours since first flight of the airplane, 

whichever occurs first, replace the 4 engine 

mount bolts and associated nuts, in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014. 

(ii) For Airbus Model A330–200 and –300 

series airplanes with an average flight time of 

132 minutes or lower and having 

accumulated less than 1,950 flight cycles and 

less than 20,210 flight hours since first flight 

of the airplane: Before further flight, retorque the affected engine mount bolt, and 

within 2,350 flight cycles or 24,320 flight 

hours since first flight of the airplane, 

whichever occurs first, replace the 4 engine 

mount bolts and associated nuts, in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014. 

(iii) For Airbus Model A330–200 Freighter 

series airplanes having accumulated less than 

2,140 flight cycles and less than 6,600 flight 

hours since first flight of the airplane: Before 

further flight, re-torque the affected engine 

mount bolt and within 2,140 flight cycles or 

6,600 flight hours since first flight of the 

airplane, whichever occurs first, replace the 

4 engine mount bolts and associated nuts, in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014. 

(iv) For airplanes identified in paragraphs 

(h)(2)(iv)(A), (h)(2)(iv)(B), and (h)(2)(iv)(C) of 

this AD: Before further flight, replace the 4 

engine mount bolts and associated nuts in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014. 

(A) Airbus Model A330–200 and –300 

series airplanes with an average flight time of 

greater than 132 minutes and having 

accumulated 2,350 flight cycles or more or 

24,320 flight hours or more since first flight 

of the airplane. 

(B) Airbus Model A330–200 and –300 

series airplanes with an average flight time of 

132 minutes or lower and having 

accumulated 1,950 flight cycles or more or 

20,210 flight hours or more since first flight 

of the airplane. 

(C) Airbus Model A330–200 Freighter 

series airplanes having accumulated 2,140 

flight cycles or more or 6,600 flight hours or 

more since first flight of the airplane. 

(3) If, during the torque check required by 

paragraph (h)(1) of this AD, two or more 

FWD engine mount bolts are found that 

rotate: Before further flight, replace the 4 

engine mount bolts and associated nuts in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014. 

(4) If, during the torque check required by 

paragraph (h)(1) of this AD, one or more FWD 

engine mount bolts are found fully broken: 

Before further flight, replace the 4 engine 

mount bolts and associated nuts in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014, except 

as required by paragraph (m)(2) of this AD. 

(5) If, during the torque check required by 

paragraph (h)(1) of this AD, only one AFT 

engine mount bolt is found that rotates: 

Before further flight, re-torque the affected 

engine mount bolt, and replace the 4 engine 

mount bolts and associated nuts at the next 

engine removal, in accordance with the 

instructions of Section 4.2.3, ‘‘Findings,’’ of 

Airbus AOT A71L004–14, Revision 01, dated 

April 7, 2014. 

(6) If, during the torque check required by 

paragraph (h)(1) of this AD, two or more AFT 

engine mount bolts are found that rotate: 

Before further flight, replace the 4 engine 

mount bolts and associated nuts in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014. 

(7) If, during the torque check required by 

paragraph (h)(1) of this AD, one or more AFT 

engine mount bolts are found fully broken: 

Before further flight, replace the 4 engine 

mount bolts and associated nuts in 

accordance with the instructions of Section 

4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 

14, Revision 01, dated April 7, 2014, except 

as required by paragraph (m)(2) of this AD. 


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36446 Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 

(i) Clarification of Concurrent Actions for 

Airbus Model A330–223F, A330–223, A330– 

321, A330–322, and A330–323 Airplanes 

Equipped With Pratt and Whitney (PW) 

Engines 

AD 2013–14–04, Amendment 39–17509 

(78 FR 68352, November 14, 2013), requires 

a torque check of FWD engine mount bolts 

using Airbus Service Bulletin A330–71–3028, 

Revision 01, dated February 20, 2012. If 

accomplishing the torque check of FWD 

engine mount bolts, as specified in Airbus 

Service Bulletin A330–71–3028, within the 

compliance times specified in paragraph (g) 

of AD 2013–14–04, perform the torque check 

of the AFT engine mount bolts at the same 

time as required by paragraph (h)(1) of this 

AD. 

(j) Action for Airbus Model A330 Airplanes 

Equipped With General Electric (GE) 

Engines 

(1) For Airbus Model A330–200, –200 

Freighter, and –300 series airplanes equipped 

with GE engines: Within 2,000 flight hours 

after the effective date of this AD, accomplish 

a one-time torque check of the FWD and AFT 

engine mount bolts on each affected engine, 

at the locations specified in, and in 

accordance with the instructions of Section 

4.2.2, ‘‘Inspection Requirements,’’ of Airbus 

AOT A71L006–14, dated July 22, 2014. 

(2) If, during the torque check required by 

paragraph (j)(1) of this AD, only one FWD 

engine mount bolt is found that rotates: Do 

the actions specified in paragraphs (j)(2)(i) 

and (j)(2)(ii) of this AD, as applicable. 

(i) For airplanes that have accumulated less 

than 4,000 flight cycles and less than 30,800 

flight hours since first flight of the airplane: 

Before further flight, re-torque affected FWD 

engine mount bolt(s), in accordance with the 

instructions of Section 4.2.3, ‘‘Findings,’’ of 

Airbus AOT A71L006–14, dated July 22, 

2014, and, within 4,000 flight cycles or 

30,800 flight hours since first flight of the 

airplane, whichever is first, replace the 5 

engine mount bolts, as applicable, and their 

associated nuts with new engine mount bolts 

and nuts in accordance with the instructions 

of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT 

A71L006–14, dated July 22, 2014. 

(ii) For airplanes that have accumulated 

4,000 flight cycles or more or 30,800 flight 

hours or more since first flight of the 

airplane: Before further flight, replace the 5 

FWD engine mount bolts, as applicable, and 

their associated nuts with new engine mount 

bolts and nuts in accordance with the 

instructions of Section 4.2.3, ‘‘Findings,’’ of 

Airbus AOT A71L006–14, dated July 22, 

2014. 

(3) If, during the torque check required by 

paragraph (j)(1) of this AD, two or more FWD 

engine mount bolts are found that rotate: 

Repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (p)(1) of this AD. 

(4) If, during the torque check required by 

paragraph (j)(1) of this AD, one or more FWD 

engine mount bolts are found fully broken: 

Repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (p)(1) of this AD. 

(5) If, during the torque check required by 

paragraph (j)(1) of this AD, only one AFT 

engine mount bolt is found that rotates: 

Before further flight, re-torque the affected 

AFT engine mount bolt(s) in accordance with 

the instructions of Section 4.2.3, ‘‘Findings,’’ 

of Airbus AOT A71L006–14, dated July 22, 

2014, and, at the next engine removal, 

replace the 4 engine mount bolts and 

associated nuts with new engine mount bolts 

and nuts in accordance with the instructions 

of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT 

A71L006–14, dated July 22, 2014. 

(6) If, during the torque check required by 

paragraph (j)(1) of this AD, two or more AFT 

engine mount bolts are found that rotate: 

Repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (p)(1) of this AD. 

(7) If, during the torque check required by 

paragraph (j)(1) of this AD, one or more AFT 

engine mount bolts are found fully broken: 

Before further flight, do all applicable 

corrective actions in accordance with the 

instructions of Section 4.2.3, ‘‘Findings,’’ of 

Airbus AOT A71L006–14, dated July 22, 

2014, except as required by paragraph (m)(2) 

of this AD. 

(k) Action for Airbus Model A330 Airplanes 

Equipped With Rolls-Royce (RR) Trent 700 

Engines 

(1) For Airbus Model A330–200, –200 

Freighter, and –300 series airplanes equipped 

with RR Trent 700 Engines: Within 2,000 

flight hours after the effective date of this AD, 

accomplish a one-time torque check of the 

FWD and AFT engine mount bolts on each 

affected engine, at the locations specified in, 

and in accordance with the instructions of 

Section 4.2.2, ‘‘Inspection Requirements,’’ of 

Airbus AOT A71L005–14, Revision 01, dated 

December 11, 2014. 

(2) If, during the torque check required by 

paragraph (k)(1) of this AD, any discrepancy 

is detected (one engine mount bolt rotates, 

two or more engine mount bolts rotate, or one 

or more engine mount bolts are fully broken): 

Within the compliance time specified in 

Airbus AOT A71L005–14, Revision 01, dated 

December 11, 2014, accomplish all 

applicable corrective actions in accordance 

with the instructions of Section 4.2.3, 

‘‘Findings,’’ of Airbus AOT A71L005–14, 

Revision 01, dated December 11, 2014, 

except as required by paragraphs (m)(1) and 

(m)(2) of this AD. 

(l) Action for Airbus Model A340–541 and 

–642 Airplanes Equipped With RR Trent 500 

Engines 

(1) For Airbus Model A340–541 and –642 

airplanes equipped with RR Trent 500 

Engines: Within 2,000 flight hours after the 

effective date of this AD, accomplish a onetime torque check of FWD and AFT engine 

mount bolts on each affected engine, at the 

locations specified in, and in accordance 

with the instructions of Section 4.2.2, 

‘‘Inspection requirements,’’ of Airbus AOT 

A71L008–14, Revision 01, dated December 

18, 2014. 

(2) If, during the torque check required by 

paragraph (l)(1) of this AD, any discrepancy 

is detected (one engine mount bolt rotates, 

two or more engine mount bolts rotate, or one 

or more engine mount bolts are fully broken): 

Within the compliance time specified in 

Airbus AOT A71L008–14, Revision 01, dated 

December 18, 2014, accomplish all 

applicable corrective actions, in accordance 

with the instructions of Section 4.2.3, 

‘‘Findings,’’ of Airbus AOT A71L008–14, 

Revision 01, dated December 18, 2014, 

except as required by paragraphs (m)(1) and 

(m)(2) of this AD. 

(m) Service Information Exceptions 

(1) Where Airbus AOTs A71L005–14, 

Revision 01, dated December 11, 2014; 

A71L006–14, dated July 22, 2014; and 

A71L008–14, Revision 01, dated December 

18, 2014; specify to contact Airbus for further 

actions, before further flight, repair 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). 

(2) Where Airbus AOT A71L004–14, 

Revision 01, dated April 7, 2014; AOT 

A71L005–14, Revision 01, dated December 

11, 2014; AOT A71L006–14, dated July 22, 

2014; and AOT A71L008–14, Revision 01, 

dated December 18, 2014, specify actions ‘‘if 

one pylon bolt fully broken,’’ this AD 

requires that those actions be done if one or 

more engine mount bolt is found fully broken 

during any torque check required by 

paragraph (h)(1), (j)(1), (k)(1) or (l)(1) of this 

AD. 

(n) Reporting 

At the applicable time specified in 

paragraphs (n)(1) and (n)(2) of this AD: After 

accomplishment of any torque check 

required by paragraphs (h), (j), (k), and (l) of 

this AD, report all inspection results to 

Airbus, including no findings, in accordance 

with the ‘‘Reporting’’ section of the 

applicable service information specified in 

paragraphs (h), (j), (k), and (l) of this AD. 

(1) If the torque check was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the torque check. 

(2) If the torque check was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(o) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus AOT 

A71L004–14, dated April 1, 2014 (for Airbus 

Model A330 Airplanes Equipped with PW 

Engines), which is not incorporated by 

reference in this AD. 

(2) This paragraph provides credit for the 

actions required by paragraph (k) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus AOT 

A71L005–14, dated September 29, 2014 (for 

Airbus Model A330 Airplanes Equipped with 

RR Trent 700 Engines), which is not 

incorporated by reference in this AD. 

(3) This paragraph provides credit for the 

actions required by paragraph (l) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus AOT 

A71L008–14, dated September 29, 2014 (for 

Airbus Model A340 Airplanes Equipped with 

RR Trent 500 Engines), which is not 

incorporated by reference in this AD. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 36447 

(p) 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 with14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone 

425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: 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 

EASA; or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(q) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2015–0082, dated May 11, 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–2015–7533. 

(r) 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 AOT A71L004–14, Revision 01, 

dated April 7, 2014. 

(ii) Airbus AOT A71L005–14, Revision 01, 

dated December 11, 2014. 

(iii) Airbus AOT A71L006–14, dated July 

22, 2014. 

(iv) Airbus AOT A71L008–14, Revision 01, 

dated December 18, 2014. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness. A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(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. 2016–12056 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–2015–8466; Directorate 

Identifier 2015–NM–045–AD; Amendment 

39–18542; AD 2016–11–15] 

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 all 

Fokker Services B.V. Model F28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by the need for more 

restrictive fuel system airworthiness 

limitations. This AD requires revising 

the maintenance program or inspection 

program, as applicable, to incorporate 

certain fuel system airworthiness 

limitations. We are issuing this AD to 

reduce 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 is effective July 12, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication 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 

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– 

8466. 

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– 

8466; 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: 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 all Fokker Services B.V. Model 

F28 Mark 0070 and 0100 airplanes. The 

NPRM published in the Federal 

Register on January 20, 2016 (81 FR 

3059) (‘‘the NPRM’’). The NPRM was 

prompted by the need for more 

restrictive fuel system airworthiness 


jstallworth on DSK7TPTVN1PROD with RULES