45462 Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Unsafe Condition 

This AD was prompted by a report of fuel 

leaking onto the hot exhaust portion of the 

engine as a result of an unintended leak path 

from the leading edge through the pylons. We 

are issuing this AD to prevent fuel leaking 

from an unintended drain path from the 

leading edge through the pylons and onto the 

hot engine parts or brakes, which could lead 

to a major ground fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation of Inboard and Outboard 

Seal Dams 

Within 60 months after the effective date 

of this AD, install new seal dams in the 

inboard and outboard corners of the aft pylon 

frame on the left and right engines, including 

a general visual inspection to detect damage 

of the outboard blade seal, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin B787–81205– 

SB540004–00, Issue 001, dated October 24, 

2014. Do all applicable corrective actions 

before further flight. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (i)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Related Information 

(1) For more information about this AD, 

contact Sherry Vevea, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6514; fax: 425–917–6590; 

email: sherry.vevea@faa.gov. 

(2) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.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. 

Issued in Renton, Washington, on July 22, 

2015. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18561 Filed 7–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2963; Directorate 

Identifier 2015–NM–016–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 all 

Airbus Model A319–131, –132, and 

–133 airplanes; Model A320–232 and 

–233 airplanes; and Model A321–131, 

–231, and –232 airplanes. This proposed 

AD was prompted by reports of forward 

engine mount attachment pins that were 

manufactured from discrepant raw 

material. This proposed AD would 

require identification and replacement 

of affected forward engine mount 

attachment pins. We are proposing this 

AD to prevent failure of a forward 

engine mount attachment pin, possible 

loss of an engine in-flight, and 

consequent reduced controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by September 14, 

2015. 

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 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus, Airworthiness Office—EIAS, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. For 

Goodrich Aerostructures service 

information identified in this proposed 

AD, contact UTC Aerospace Systems, 

ATTN: Christopher Newth—V2500 A1/ 

A5 Project Engineer, Aftermarket— 

Aerostructures; 850 Lagoon Drive, Chula 

Vista, CA; telephone 619–498–7505; 

email christopher.newth@utas.utc.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– 

2963; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

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–2015–2963; Directorate Identifier 

2015–NM–016–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 


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Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45463 

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 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0004, dated January 13, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A319–131, –132, and –133 

airplanes; Model A320–232 and –233 

airplanes; and Model A321–131, –231, 

and –232 airplanes. The MCAI states: 

A number of forward engine mount pins, 

Part Number (P/N) 740–2022–501, intended 

for IAE V2500 series engines, have been 

reported as non-compliant with the current 

certification requirements, due to a quality 

issue during manufacturing of the raw 

material. It was also determined that a batch 

of 88 affected pins are installed on in-service 

aeroplanes fitted with forward engine mount 

P/N 745–2010–503 and the serial numbers (s/ 

n) of the affected pins and the [manufacturer 

serial number] MSN of the related aeroplanes 

have been identified. 

This condition, if not corrected, could lead 

to forward engine mount pin failure, possibly 

resulting in in-flight loss of an engine and 

consequent reduced control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires identification of the 

affected forward engine mount pins and 

removal from service [replacement] of those 

pins. 

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– 

2963. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–71–1064, dated November 5, 

2014; and Goodrich Aerostructures has 

issued Service Bulletin V2500–NAC– 

71–0323, dated September 18, 2014. The 

service information describes 

procedures for an inspection to 

determine the serial number of the 

attachment pins for the forward engine 

mount crossbeam to main beam for each 

engine, and replacement of affected 

pins. 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. 

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. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The procedures and tests 

identified as RC (required for 

compliance) in any service information 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified Airbus service information, 

procedures and tests identified as RC 

must be done to comply with the 

proposed AD. However, procedures and 

tests that are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 922 airplanes of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $156,740, or $170 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 4 work-hours and require parts 

costing $1,724, for a cost of $2,064 per 

attachment pin replacement. We have 

no way of determining the number of 

aircraft that might need this action. 

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, 


Lhorne on DSK7TPTVN1PROD with PROPOSALS
45464 Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 

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–2015–2963; 

Directorate Identifier 2015–NM–016–AD. 

(a) Comments Due Date 

We must receive comments by September 

14, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

all manufacturer serial numbers. 

(1) Model A319–131, –132, and –133 

airplanes. 

(2) Model A320–232 and –233 airplanes. 

(3) Model A321–131, –231, and –232 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Power Plant. 

(e) Reason 

This AD was prompted by reports of 

forward engine mount attachment pins that 

were manufactured from discrepant raw 

material. We are issuing this AD to prevent 

failure of a forward engine mount attachment 

pin, possible loss of an engine in-flight, and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Identification of Part Numbers for 

Forward Engine Mount and Attachment Pins 

Except as provided by paragraph (i) of this 

AD, at the earliest of the times specified in 

paragraphs (g)(1) through (g)(4) of this AD: 

For each engine, identify the part number of 

the forward engine mount, and the part 

number and serial number of the attachment 

pin for that forward engine mount, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1064, dated November 5, 2014; and 

Goodrich Aerostructures Service Bulletin 

V2500–NAC–71–0323, dated September 18, 

2014. A review of airplane maintenance 

records is acceptable in lieu of this 

identification if the part number of the 

forward engine mount, and the part number 

and serial number of the attachment pin for 

that forward engine mount can be 

conclusively determined from that review. If 

any part number of the forward engine 

mount, or part number or serial number of 

the attachment pins for the forward engine 

mount, cannot be identified: At the earliest 

of the times specified in paragraphs (g)(1) 

through (g)(4) of this AD, contact 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), for identification 

information. 

(1) Within 24 months after the effective 

date of this AD. 

(2) At the next engine removal after the 

effective date of this AD. 

(3) Within 7,500 flight hours after the 

effective date of this AD. 

(4) Within 5,000 flight cycles after the 

effective date of this AD. 

(h) Corrective Actions 

If, during any identification required by 

paragraph (g) of this AD, a forward engine 

mount having part number (P/N) 745–2010– 

503 is found, and the attachment pin has P/ 

N 740–2022–501 with any serial number that 

is included in figure 1 to paragraphs (h) and 

(j) of this AD: At the earliest of the times 

specified in paragraphs (g)(1) through (g)(4) 

of this AD, replace the affected attachment 

pin with a serviceable part having a part 

number other than P/N 740–2022–501, and 

having a serial number that is not identified 

in figure 1 to paragraphs (h) and (j) of this 

AD, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1064, dated November 5, 2014; and 

Goodrich Aerostructures Service Bulletin 

V2500–NAC–71–0323, dated September 18, 

2014. 

FIGURE 1 TO PARAGRAPHS (h) AND (j) 

OF THIS AD—PART NUMBERS AND

SERIAL NUMBERS OF AFFECTED

FORWARD ENGINE MOUNTS AND ATTACHMENT PINS

Serial Nos. 

Attachment Pin 

(P/N 740–2022–501) 

Forward Engine 

Mount 

(P/N 745–2010–503) 

1396SC 13665001 

1391SC 13655001 

1412SC 13689001 

1402SC 13669001 

1409SC 13683001 

1416SC 13697001 

1418SC 13701001 

1417SC 13699001 

1414SC 13693001 

FIGURE 1 TO PARAGRAPHS (h) AND (j) 

OF THIS AD—PART NUMBERS AND

SERIAL NUMBERS OF AFFECTED

FORWARD ENGINE MOUNTS AND ATTACHMENT PINS—Continued 

Serial Nos. 

Attachment Pin 

(P/N 740–2022–501) 

Forward Engine 

Mount 

(P/N 745–2010–503) 

1415SC 13695001 

1420SC 13705001 

1421SC 13707001 

1422SC 13709001 

1436SC 13737001 

1438SC 13741001 

1452SC 13769001 

1456SC 13777001 

1397SC 13667001 

1432SC 13729001 

1405SC 13675001 

1411SC 13687001 

1389SC 13651001 

1392SC 13657001 

1382SC 13637001 

1384SC 13641001 

1407SC 13679001 

1408SC 13681001 

1395SC 13663001 

1406SC 13677001 

1383SC 13639001 

1404SC 13673001 

1393SC 13659001 

1413SC 13691001 

1386SC 13645001 

1388SC 13649001 

1390SC 13653001 

1410SC 13685001 

1423SC 13711001 

1424SC 13713001 

1403SC 13671001 

1419SC 13703001 

1385SC 13643001 

1387SC 13647001 

1431SC 13727001 

1433SC 13731001 

1425SC 13715001 

1428SC 13721001 

1429SC 13723001 

1430SC 13725001 

1427SC 13719001 

1434SC 13733001 

1442SC 13749001 

1394SC 13661001 

1441SC 13747001 

1426SC 13717001 

1437SC 13739001 

1439SC 13743001 

1443SC 13751001 

1448SC 13761001 

1435SC 13735001 

1440SC 13745001 

1454SC 13773001 

1455SC 13775001 

1451SC 13767001 

1453SC 13771001 

1444SC 13753001 

1450SC 13765001 

1461SC 13787001 

1469SC 13817001 

1480SC 13839001 

1481SC 13841001 

1446SC 13757001 

1449SC 13763001 


Lhorne on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45465 

FIGURE 1 TO PARAGRAPHS (h) AND (j) 

OF THIS AD—PART NUMBERS AND

SERIAL NUMBERS OF AFFECTED

FORWARD ENGINE MOUNTS AND ATTACHMENT PINS—Continued 

Serial No. 

Attachment Pin 

(P/N 740–2022–501) 

Forward Engine 

Mount 

(P/N 745–2010–503) 

1467SC 13813001 

1445SC 13755001 

1462SC 13789001 

1464SC 13793001 

1466SC 13811001 

1470SC 13819001 

1459SC 13783001 

1463SC 13791001 

1475SC 13829001 

1458SC 13781001 

1477SC 13833001 

1474SC 13827001 

1478SC 13835001 

1479SC 13837001 

1472SC 13823001 

(i) Exception to Paragraph (g) of This AD 

For airplanes with manufacturer serial 

numbers identified in figure 2 to paragraph 

(i) of this AD: If it can be conclusively 

determined that an engine has not been 

replaced after March 1, 2011 (the date of 

manufacture of the first airplane with 

affected engine mounts), the airplane is not 

affected by the requirements of paragraphs (g) 

and (h) of this AD. 

FIGURE 2 TO PARAGRAPH (i) OF THIS

AD—AIRPLANE MANUFACTURER SERIAL NUMBERS

Airplane manufacturer serial Nos. 

4593 

4602 

4620 

4637 

4638 

4642 

4643 

4644 

4660 

4677 

4690 

4696 

4700 

4701 

4703 

4706 

4707 

4710 

4716 

4719 

4725 

4726 

4731 

4736 

4737 

4741 

4746 

4751 

4752 

FIGURE 2 TO PARAGRAPH (i) OF THIS

AD—AIRPLANE MANUFACTURER SERIAL NUMBERS—Continued 

Airplane manufacturer serial Nos. 

4753 

4754 

4755 

4757 

4761 

4762 

4772 

4773 

4774 

4775 

4779 

4782 

4783 

4784 

4786 

4788 

4790 

4791 

4798 

4804 

4813 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install on any airplane any 

engine mount attachment pin having P/N 

740–2022–501 with a serial number 

identified in figure 1 to paragraphs (h) and 

(j) of this AD. 

(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, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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 Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Special Flight Permits Prohibited 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0004, dated 

January 13, 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–2015–2963. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

5 61 93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

For Goodrich Aerostructures service 

information identified in this AD, contact 

UTC Aerospace Systems, ATTN: Christopher 

Newth—V2500 A1/A5 Project Engineer, 

Aftermarket—Aerostructures; 850 Lagoon 

Drive, Chula Vista, CA; telephone 619–498– 

7505; email christopher.newth@utas.utc.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 July 17, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18533 Filed 7–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 101 

[Docket No. FDA–2015–D–1839] 

The Food and Drug Administration’s 

Policy on Declaring Small Amounts of 

Nutrients and Dietary Ingredients on 

Nutrition Labels; Draft Guidance for 

Industry; Availability 

AGENCY: Food and Drug Administration, 

HHS. 


Lhorne on DSK7TPTVN1PROD with PROPOSALS