81216 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules 

catalogs, and in other product 

advertising literature. 

Original equipment manufacturer or 

OEM means any person who produces 

or assembles a unit of a covered product 

or covered equipment. Only one OEM is 

responsible for the manufacture 

(production or assembly) of a particular 

unit. 

■ 3. Section 429.5 is amended by adding 

paragraph (c) to read as follows: 

§ 429.5 Imported products. 

* * * * * 

(c) Any person importing a unit of a 

covered product or covered equipment 

subject to an applicable energy 

conservation standard set forth in parts 

430 or 431 of this chapter for entry into 

the United States on or after [2 YEARS 

AFTER DATE OF PUBLICATION OF 

FINAL RULE IN THE FEDERAL 

REGISTER], whether the unit is a 

component part of another product or a 

final product, must provide a 

certification of admissibility to the 

Secretary in accordance with § 429.500. 

■ 4. Section 429.7 is amended by 

revising paragraph (b) to read as follows: 

§ 429.7 Confidentiality. 

* * * * * 

(b) An individual model number is 

public information unless: 

(1) The individual model number is a 

unique model number of a commercial 

packaged boiler, commercial water 

heating equipment, commercial HVAC 

equipment or commercial refrigeration 

equipment that was developed for an 

individual customer, 

(2) The individual model number is 

not displayed on product literature, and 

(3) Disclosure of the individual model 

number would reveal confidential 

business information as described at 

§ 1004.11 of this title—in which case, 

under these limited circumstances, a 

manufacturer may identify the 

individual model number as a private 

model number on a certification report 

submitted pursuant to § 429.12(b)(6). 

* * * * * 

■ 5. Section 429.12 is amended by 

revising paragraph (b)(6) to read as 

follows: 

§ 429.12. General requirements applicable 

to certification reports. 

* * * * * 

(b) * * * 

(6) For each brand, the basic model 

number and the individual model 

number(s) in that basic model with the 

following exceptions: For walk-in 

coolers, the basic model number for 

each brand must be submitted. For 

distribution transformers, the basic 

model number or kVA grouping model 

number (depending on the certification 

method) for each brand must be 

submitted. For commercial HVAC, WH, 

and refrigeration equipment, an 

individual model number may be 

identified as a ‘‘private model number’’ 

if it meets the requirements of 

§ 429.7(b). 

* * * * * 

■ 6. Section 429.500 is added to read as 

follows: 

§ 429.500. Certification of admissibility. 

(a) A certification of admissibility 

submitted pursuant to § 429.5(c) must 

meet the provisions of this section. 

(b) The certification must be 

submitted through the Automated 

Commercial Environment (ACE) of the 

U.S. Customs and Border Protection 

(CBP) before the entry of the unit(s) at 

the port of arrival. 

(c) The certification must include 

whether the basic model of the product 

or equipment being imported has been 

certified to DOE as compliant with all 

applicable energy conservation 

standards; 

(d) If the importer has not submitted 

a certification report for the basic model 

of the product or equipment being 

imported pursuant to § 429.12, the 

certification of admissibility must 

include: 

(1) The type of product or equipment 

(using a three-digit code corresponding 

to the applicable section in 10 CFR part 

429, subpart B); 

(2) The brand name of the covered 

product or equipment; 

(3) The individual model number of 

the covered product or equipment; 

(4) Whether the covered product or 

equipment being imported is a final 

product or a component of a final 

product and, if the covered product or 

equipment is a component, the brand 

name and individual model number of 

the final product; 

(5) The original equipment 

manufacturer (OEM) of the covered 

product or equipment being imported as 

defined in § 429.2 and, in the case of 

electric motors, the Compliance 

Certification number; and 

(6) A contact name and email address 

of the importer of record. 

(e) If the importer has submitted a 

certification report for the basic model 

of the product or equipment being 

imported pursuant to § 429.12, the 

certification of admissibility must 

include: 

(1)The CCMS ticket number of the 

most recent certification submission; 

(2)The CCMS attachment 

identification number assigned to the 

certification submission; 

(3) The line number in the submission 

corresponding to the basic model 

certified; and 

(4) If the covered product or 

equipment is a component of a final 

product, the brand name and individual 

model number of the final product. 

[FR Doc. 2015–32796 Filed 12–28–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7533; Directorate 

Identifier 2015–NM–080–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes, Model A330–200 Freighter 

series airplanes, and Airbus Model 

A340–541 and A340–642 airplanes. 

This proposed AD was prompted by a 

report of an under-torqued forward 

engine mount bolt. This proposed AD 

would require a one-time torque check 

of the forward and aft engine mount 

bolts, and corrective actions if 

necessary. We are proposing 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: We must receive comments on 

this proposed AD by February 12, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules 81217 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 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. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–7533; Directorate Identifier 

2015–NM–080–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

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 Airbus 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 

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 Pratt 

& Whitney (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, [corrective actions] 

re-torque of the affected bolt(s) and/or 

replacement of all four bolts and associated 

nuts. 

Findings (or discrepancies) include 

one bolt that is loose or able to rotate, 

two or more bolts that are loose or able 

to rotate, or one or more pylon bolts that 

are fully broken. Corrective actions 

include re-torqueing the affected bolt(s), 

and replacing all bolts and associated 

nuts with new bolts and nuts on the 

engine where the loose or fully broken 

bolt(s) were detected. This proposed AD 

specifies reporting of all findings 

(including no discrepancies). The 

corrective actions include re-torqueing 

loose bolts before further flight. The 

compliance times for replacing loose or 

fully broken bolts ranges, depend on 

airplane configuration, and range from 

before further flight if more than one 

bolt rotates or is fully broken to no later 

than 2,350 flight cycles or 24,320 flight 

hours since first flight of the airplane, if 

only one bolt rotates. 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. 

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 pylon bolts at four 

positions at the forward engine pylon 1 

and pylon 2 of Airbus Model A330 

series airplanes having Pratt and 

Whitney 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 pylon 

bolts at four positions at the forward 

engine pylon 1 and pylon 2 of Airbus 

Model A330 series airplanes having 

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 pylon 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 pylon 

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 of 

this NPRM. 

Other Related Rulemaking 

On June 21, 2013, we issued AD 

2013–14–04, Amendment 39–17509 (78 

FR 68352, November 14, 2013). AD 

2013–14–04 requires a torque check of 

forward engine mount bolts, and 

replacement if necessary on all Airbus 

Model A330–223F, –223, –321, –322, 

and –323 airplanes. AD 2013–14–04 was 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
81218 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules 

prompted by a fatigue load analysis that 

determined that the inspection interval 

for certain pylon bolts must be reduced. 

We issued AD 2013–04–04 to detect and 

correct loose or broken bolts, which 

could lead to engine detachment inflight, and damage to the airplane. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 55 airplanes of U.S. registry. 

We also estimate that it would take 

about 12 work-hours per product to 

comply with the basic requirements of 

this proposed AD, and 1 work-hour per 

product to report torque check findings. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $60,755, or $1,105 

per product. 

In addition, we estimate that any 

necessary follow-on actions would 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 

OMB control number. The control 

number for the collection of information 

required by this proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed 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 proposed 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus: Docket No. FAA–2015–7533; 

Directorate Identifier 2015–NM–080–AD. 

(a) Comments Due Date 

We must receive comments by February 

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 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 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules 81219 

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 Airbus 

Service Bulletin A330–71–3028, Revision 01, 

dated February 20, 2012, 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 

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 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 bolt, and, within 2,350 

flight cycles or 24,320 flight hours since first 

flight of the airplane, whichever occurs first, 

replace the 4 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 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, re-torque the 

affected bolt, and within 2,350 flight cycles 

or 24,320 flight hours since first flight of the 

airplane, whichever occurs first, replace the 

4 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 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 bolt and 

within 2,140 flight cycles or 6,600 flight 

hours since first flight of the airplane, 

whichever occurs first, replace the 4 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 

bolts and associated nuts in accordance with 

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

of AOT A71L004–14, Revision 01, dated 

April 7, 2014. 

(A) 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) 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) 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 bolts are found that rotate: Before 

further flight, replace the 4 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 

pylon bolts are found fully broken: Before 

further flight, replace the 4 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 

bolt is found that rotates: Before further 

flight, re-torque the affected bolt, and replace 

the 4 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 

bolts are found that rotate: Before further 

flight, replace the 4 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 

pylon bolts are found fully broken: Before 

further flight, replace the 4 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. 

(i) Concurrent Actions 

AD 2013–14–04, Amendment 39–17509 

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

a torque check of forward 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 within the compliance 

times specified in paragraph (g) of the FAA 

AD 2013–14–04 using Airbus Service 

Bulletin A330–71–3028, Revision 01, dated 

February 20, 2012, perform the torque check 

of the AFT engine mount bolts at the same 

time. 

(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 

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 

bolts, as applicable, and their associated nuts 

with new 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 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 

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 

pylon 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 bolt 

is found that rotates: Before further flight, retorque 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 bolts and 

associated nuts with new 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 

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 

pylon 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, 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
81220 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules 

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 bolt rotates, two or more 

bolts rotate, or one or more 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 Rolls-Royce 

Trent 500 Engines 

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

airplanes equipped with Rolls-Royce Trent 

500 Engines: Within 2,000 flight hours after 

the effective date of this AD, accomplish a 

one-time 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 bolt rotates, two or more 

bolts rotate, or one or more 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, dated September 29, 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 pylon 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 Pratt 

and Whitney 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 

Rolls-Royce 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 

Rolls-Royce Trent 500 Engines), which is not 

incorporated by reference in this AD. 

(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 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: 

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 

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. 

(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 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 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. 

(2) 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. 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. 

Issued in Renton, Washington, on 

December 18, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–32547 Filed 12–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7531; Directorate 

Identifier 2015–NM–052–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This proposed AD was 


jstallworth on DSK7TPTVN1PROD with PROPOSALS