81168 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 

Bulletin 100–25–21, Revision 01, dated 

February 26, 2013, which is not incorporated 

by reference in this AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7300; fax 

516–794–5531. 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: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2010–06R1, 

dated August 8, 2013, 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–2015–1199. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(5) and (p)(6) of this AD. 

(p) 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. 

(3) The following service information was 

approved for IBR on February 2, 2016. 

(i) Bombardier Service Bulletin 100–25–21, 

Revision 02, dated July 25, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 5, 2011, (76 FR 

17758, March 31, 2011). 

(i) Bombardier Service Bulletin A100–21– 

08, dated June 18, 2009. 

(ii) Bombardier Service Bulletin 100–25– 

14, dated June 30, 2008. 

(iii) Bombardier Service Bulletin 100–25– 

21, dated June 30, 2008. 

(iv) Bombardier Temporary Revision (TR) 

5–2–53, dated October 1, 2009, to Section 5– 

10–40, ‘‘Certification Maintenance 

Requirements,’’ in Part 2 of Chapter 5 of 

Bombardier Challenger 300 BD–100 Time 

Limits/Maintenance Checks. 

(5) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(6) 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. 

(7) 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 

December 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32080 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–2014–0648; Directorate 

Identifier 2013–NM–136–AD; Amendment 

39–18344; AD 2015–25–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010–06– 

04, for certain Airbus Model A300 B2– 

1C, B2–203, B2K–3C, B4–103, B4–203, 

B4–2C airplanes; Model A310 series 

airplanes; Model A300 B4–600 series 

airplanes; and Model A300 B4–600R 

series airplanes. AD 2010–06–04 

required repetitive inspections to detect 

cracks of the pylon side panels (upper 

section) at rib 8; and corrective actions 

if necessary. This new AD continues to 

require repetitive inspections for 

cracking of the pylons 1 and 2 side 

panels (upper section) at rib 8 with 

reduced compliance times, and 

corrective actions if necessary. This AD 

also requires repetitive post-repair and 

post-modification inspections and 

repair if necessary. This AD also 

removes certain airplanes having a 

certain modification from the 

applicability. This AD was prompted by 

reports of cracks found on pylon side 

panels at rib 8 and a fleet survey and 

updated fatigue and damage tolerance 

analyses. We are issuing this AD to 

detect and correct cracking of pylon side 

panels (upper section) at rib 8, which 

could lead to reduced structural 

integrity of the pylon primary structure, 

which could cause detachment of the 

engine from the fuselage. 

DATES: This AD becomes effective 

February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 15, 2010 ((75 FR 

11428, March 11, 2010); corrected May 

4, 2010 (75 FR 23572)). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0648; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this final rule, contact Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

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

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 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–2014– 

0648. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–06–04, 


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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 81169 

Amendment 39–16228 ((75 FR 11428, 

March 11, 2010); corrected May 4, 2010 

(75 FR 23572)). AD 2010–06–04 applied 

to certain Airbus Model A300 B2–1C, 

B2–203, B2K–3C, B4–103, B4–203, B4– 

2C airplanes; Model A310 series 

airplanes; Model A300 B4–600 series 

airplanes; and Model A300 B4–600R 

series airplanes. The NPRM published 

in the Federal Register on September 

22, 2014 (79 FR 56526). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0136R1, dated July 30, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Airbus 

Model A300 B2–1C, B2–203, B2K–3C, 

B4–103, B4–203, B4–2C airplanes; 

Model A310 series airplanes; Model 

A300 B4–600 series airplanes; and 

Model A300 B4–600R series airplanes. 

The MCAI states: 

Cracks were found on pylon side panels 

(upper section) at rib 8 on Airbus A300, A310 

and A300–600 aeroplanes equipped with 

General Electric engines. Investigation of 

these findings indicated that this problem 

was likely to also affect aeroplanes of this 

type design with other engine installations. 

This condition, if not detected and 

corrected, could lead to reduced strength of 

the pylon primary structure, possibly 

resulting in pylon structural failure and inflight loss of an engine. 

Prompted by these findings, EASA issued 

AD 2008–0181 [http://www.regulations.gov/

#!documentDetail;D=FAA-2009-0789-0002] 

[which corresponds to FAA AD 2010–06–04, 

Amendment 39–16228 ((75 FR 11428, March 

11, 2010); corrected May 4, 2010 (75 FR 

23572))] to require repetitive detailed visual 

inspections [of the pylon side panels (upper 

section) at rib 8] and, depending on 

aeroplane configuration and/or findings, the 

accomplishment of applicable corrective 

action(s). 

Since that [EASA] AD was issued, a fleet 

survey and updated Fatigue and Damage 

Tolerance analyses have been performed in 

order to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. The 

results of these analyses have shown that the 

risk for these aeroplanes is higher than 

initially determined and consequently, the 

threshold and interval must be reduced to 

allow timely detection of these cracks and 

the accomplishment of applicable correction 

action(s). 

EASA issued AD 2013–0136 [http://

ad.easa.europa.eu/ad/2013-0136R1] which 

retained the requirements of EASA AD 2008– 

0181, which was superseded, and required 

the inspections to be accomplished within 

reduced thresholds and intervals. 

After publication of EASA AD 2013–0136, 

it appeared that Airbus Mod 03599 had no 

influence on the aeroplane configuration 

affected by this AD. At the same time Airbus 

Service Bulletin (SB) A30–54–6015 Revision 

3 was not integrally taken into account as 

this revision no longer identifies 

configuration 3 aeroplanes. 

For the reasons described above, EASA 

[AD] 2013–0136 is revised to exclude Airbus 

Mod 03599 from the applicability and to 

delete the reference to the configuration 3 for 

A300–600 aeroplanes. 

Corrective actions include doing a 

repair. This AD also provides an 

optional modification (installing a 

doubler), which would terminate the 

repetitive inspections. Required actions 

also include repetitive post-repair and 

post-modification inspections and 

repair if necessary. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0648-

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 56526, 

September 22, 2014) and the FAA’s 

response. 

Request To Revise Method Used To 

Determine Compliance Times 

United Parcel Service (UPS) requested 

that we revise the proposed compliance 

times to be less complex. UPS stated 

that the proposed compliance times 

contain a method known as ‘‘Average 

Flight Time’’ (AFT) which results in a 

variable flight hour limit and adds 

unnecessary complexity to the threshold 

table and subsequent inspection actions. 

UPS added that use of the AFT method, 

along with a lack of standard procedures 

for implementing the AFT method 

would create uncertainty for operators 

and inspectors trying to determine the 

correct compliance time. UPS stated 

that in review of prior FAA ADs, 

including AD 98–18–02, Amendment 

39–10718 (63 FR 45689, August 27, 

1998), that the FAA does not concur 

with the AFT compliance time 

methodology as ‘‘. . . such adjustments 

may not address the unsafe condition in 

a timely manner’’ and ‘‘. . . they (AFT 

compliance times) do not fit into the AD 

tracking process for operators or for 

Principle Maintenance Inspectors 

(PMIs) attempting to ascertain 

compliance with ADs.’’ 

UPS compiled a table of fixed 

compliance times that it suggested 

would be simpler to use instead of the 

proposed AFT-based compliance times. 

We disagree with the commenter’s 

request to revise the compliance times 

in this AD. The compliance times, as 

proposed, use fixed flight-cycle and 

flight-hour compliance times. For only 

Model A310 series airplanes, the 

compliance times depend on whether 

airplanes are short range or long range 

airplanes. We acknowledge that this 

causes additional complexity in tracking 

and forecasting airplane utilization; 

however, the inspection schedule was 

created by Airbus to offer operators the 

greatest flexibility. Operators may elect 

to inspect within the range that 

complies with both the long range and 

short range utilization in order to reduce 

the complexity. We have not changed 

this AD in this regard. 

Regarding AD 98–18–02, Amendment 

39–10718 (63 FR 45689, August 27, 

1998), at the time the FAA issued AD 

98–18–02, the required actions in 

Airbus Industrie Service Bulletin A300– 

57–6027, Revision 2, dated September 

13, 1994, contained inspection 

thresholds and intervals based on 

airplane flight cycles, and provided 

instructions for adjusting the flight cycle 

threshold and interval using each 

individual airplane’s AFT utilization. 

The FAA did not agree with the AFT 

method because it could result in a 

different inspection threshold and 

interval for each individual airplane, 

and the FAA did not agree with 

adjusting a flight cycle based threshold 

and interval using the average flight 

time utilization without also having a 

related flight hour based threshold and 

interval. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

56526, September 22, 2014) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 56526, 

September 22, 2014). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. The service 

information describes procedures for 

repetitive inspections for cracking of the 

pylons 1 and 2 side panels (upper 

section) at rib 8 with reduced 

compliance times, and corrective 

actions if necessary. This service 

information also describes procedures 

for post-modification and post-repair 

detailed inspections for cracking, as 

applicable, of the left-hand (LH) and 

right-hand (RH) side panels of pylons 1 

and 2, and repair if necessary. This 


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81170 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 

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. 

• Airbus Service Bulletin A300–54– 

0075, Revision 03, excluding 

Appendixes 1, 2, 3, and 5; including 

Appendix 4; dated March 27, 2013. 

• Airbus Service Bulletin A310–54– 

2018, Revision 03, excluding 

Appendixes 1, 2, 3, and 5; including 

Appendix 4; dated April 11, 2013. 

• Airbus Service Bulletin A300–54– 

6015, Revision 03, excluding 

Appendixes 1, 2, 3, and 5; including 

Appendix 4; dated April 11, 2013. 

Airbus has also issued the following 

service information. This service 

information describes procedures for 

modifying by installing a doubler on the 

LH pylon 1 and RH pylon 2, on pylon 

side panels (upper section), at rib 8. 

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. 

• Airbus Service Bulletin A300–54– 

0081, dated August 11, 1993. 

• Airbus Service Bulletin A310–54– 

2024, dated August 11, 1993. 

• Airbus Service Bulletin A300–54– 

6021, Revision 02, dated May 21, 2008. 

Costs of Compliance 

We estimate that this AD affects 156 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection [retained actions from 

AD 2010–06–04, Amendment 

39–16228 ((75 FR 11428, 

March 11, 2010); corrected 

May 4, 2010 (75 FR 23572))].

4 work-hours × $85 per hour = $340 .......... $0 $340 .......................... $53,040. 

Inspection [new actions] .............. 24 work-hours × $85 per hour = $2,040 per 

inspection cycle.

0 $2,040 per inspection 

cycle.

$318,240 per inspection cycle. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair .................................. 58 work-hours × $85 per hour = $4,930 ....................... $3,910 ................................ $8,840. 

Optional Modification ........... Up to 48 work-hours × $85 per hour = $4,080 ............. Up to $1,026 ...................... Up to $5,106. 

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 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/#!docketDetail;D=

FAA-2014-0648; 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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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 

removing Airworthiness Directive (AD) 

2010–06–04, Amendment 39–16228 ((75 

FR 11428, March 11, 2010); corrected 


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May 4, 2010 (75 FR 23572)), and adding 

the following new AD: 

2015–25–06 Airbus: Amendment 39– 

18344. Docket No. FAA–2014–0648; 

Directorate Identifier 2013–NM–136–AD. 

(a) Effective Date 

This AD becomes effective February 2, 

2016. 

(b) Affected ADs 

This AD replaces AD 2010–06–04, 

Amendment 39–16228 ((75 FR 11428, March 

11, 2010); corrected May 4, 2010 (75 FR 

23572)). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category. 

(1) Airbus Model A300 B2–1C, B2–203, 

B2K–3C, B4–103, B4–203, and B4–2C 

airplanes, on which Airbus Modification 

02434 has been embodied in production. 

(2) Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes, 

except those on which Airbus Modification 

10432 has been embodied in production. 

(3) Airbus Model A300 B4-601, B4-603, B4- 

605R, B4-620, B-622, and B4-622R airplanes, 

except those on which Airbus Modification 

10432 has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Reason 

This AD was prompted by reports of cracks 

found on pylon side panels at rib 8 and a 

fleet survey and updated fatigue and damage 

tolerance analyses. We are issuing this AD to 

detect and correct cracking of pylon side 

panels (upper section) at rib 8, which could 

lead to reduced structural integrity of the 

pylon primary structure, which could cause 

detachment of the engine from the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Actions and Compliance With 

Revised Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2010–06–04, Amendment 

39–16228 ((75 FR 11428, March 11, 2010); 

corrected May 4, 2010 (75 FR 23572)), with 

revised service information. Accomplishing 

the initial inspection required by paragraph 

(h) of this AD terminates the requirements of 

this paragraph. 

(1) For Configuration 01 airplanes as 

identified in the applicable service bulletin 

identified in paragraph (g)(9) of this AD: At 

the applicable time specified in table 1 to 

paragraph (g) of this AD, except as required 

by paragraphs (g)(2) and (g)(3) of this AD, 

perform a detailed visual inspection of the 

pylons 1 and 2 side panels (upper section) at 

rib 8, in accordance with paragraph 3.B. of 

the Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(9)(i) through (g)(9)(iii) of this 

AD or paragraphs (k)(1), (k)(2), or (k)(3) of 

this AD. Repeat the inspection at the time 

specified in table 1 to paragraph (g) of this 

AD. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES

For Model— That have accumulated— Inspect before the 

accumulation of— Or within— 

And repeat the inspection 

at intervals not to 

exceed— 

Whichever occurs later 

A300 B2–1C, B2–203, and 

B2K–3C airplanes.

≤17,500 total flight cycles 1 5,350 total flight cycles ..... 2,500 flight cycles 2 ........... 4,300 flight cycles. 

A300 B2–1C, B2–203, and 

B2K–3C airplanes.

>17,500 total flight cycles 1 20,000 total flight cycles or 

40,000 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 4,300 flight cycles. 

A300 B4–103, B4–203, 

and B4–2C airplanes.

≤18,000 total flight cycles 1 5,350 total flight cycles ..... 2,000 flight cycles 2 ........... 4,300 flight cycles. 

A300 B4–103, B4–203, 

and B4–2C airplanes.

>18,000 total flight cycles 1 20,000 total flight cycles or 

40,000 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 4,300 flight cycles. 

A300 B4–601, B4–603, 

B4–605R, B4–620, B4– 

622, and B4–622R airplanes.

≤18,000 total flight cycles 1 4,200 total flight cycles ..... 2,000 flight cycles 2 ........... 3,600 flight cycles. 

A300 B4–601, B4–603, 

B4–605R, B4–620, B4– 

622, and B4–622R airplanes.

>18,000 total flight cycles 1 20,000 total flight cycles or 

40,000 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 3,600 flight cycles. 

A310–200 airplanes with 

GE CF6–80A3 or Pratt & 

Whitney engines.

≤18,000 total flight cycles 1 9,700 total flight cycles or 

19,400 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 6,700 flight cycles or 

13,400 flight hours, 

whichever occurs first. 

A310–200 airplanes with 

GE CF6–80A3 or Pratt & 

Whitney engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 6,700 flight cycles or 

13,400 flight hours, 

whichever occurs first. 

A310–200 airplanes with 

GE CF6–80C2 engines.

≤18,000 total flight cycles 1 7,800 total flight cycles or 

15,600 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 5,800 flight cycles or 

11,600 flight hours, 

whichever occurs first. 

A310–200 airplanes with 

GE CF6–80C2 engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 5,800 flight cycles or 

11,600 flight hours, 

whichever occurs first. 

A310–300 SR 3 airplanes 

with Pratt & Whitney 

JT9D engines.

≤18,000 total flight cycles 1 8,600 total flight cycles or 

24,000 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 6,700 flight cycles or 

18,700 flight hours, 

whichever occurs first. 

A310–300 SR 3 airplanes 

with Pratt & Whitney 

JT9D engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 6,700 flight cycles or 

18,700 flight hours, 

whichever occurs first. 

A310–300 SR 3 airplanes 

with GE engines.

≤18,000 total flight cycles 1 7,000 total flight cycles or 

19,600 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 5,700 flight cycles or 

15,900 flight hours, 

whichever occurs first. 

A310–300 SR 3 airplanes 

with GE engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 5,700 flight cycles or 

15,900 flight hours, 

whichever occurs first. 


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81172 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES—Continued 

For Model— That have accumulated— Inspect before the 

accumulation of— Or within— 

And repeat the inspection 

at intervals not to 

exceed— 

Whichever occurs later 

A310–300 SR 3 airplanes 

with Pratt & Whitney 

4000 engines.

≤18,000 total flight cycles 1 7,000 total flight cycles or 

19,600 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 5,800 flight cycles or 

16,200 flight hours, 

whichever occurs first. 

A310–300 SR 3 airplanes 

with Pratt & Whitney 

4000 engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 5,800 flight cycles or 

16,200 flight hours, 

whichever occurs first. 

A310–300 LR 4 airplanes 

with Pratt & Whitney 

JT9D engines.

≤18,000 total flight cycles 1 5,900 total flight cycles or 

29,500 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 6,000 flight cycles or 

30,300 flight hours, 

whichever occurs first. 

A310–300 LR 4 airplanes 

with Pratt & Whitney 

JT9D engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 6,000 flight cycles or 

30,300 flight hours, 

whichever occurs first. 

A310–300 LR 4 airplanes 

with GE engines.

≤18,000 total flight cycles 1 4,800 total flight cycles or 

24,100 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 5,100 flight cycles or 

25,500 flight hours, 

whichever occurs first. 

A310–300 LR 4 airplanes 

with GE engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 5,100 flight cycles or 

25,500 flight hours, 

whichever occurs first. 

A310–300 LR 4 airplanes 

with Pratt & Whitney 

4000 engines.

≤18,000 total flight cycles 1 4,800 total flight cycles or 

24,000 total flight hours, 

whichever occurs first.

1,500 flight cycles 2 ........... 5,200 flight cycles or 

26,300 flight hours, 

whichever occurs first. 

A310–300 LR 4 airplanes 

with Pratt & Whitney 

4000 engines.

>18,000 total flight cycles 1 19,500 total flight cycles or 

55,500 total flight hours, 

whichever occurs first.

250 flight cycles 2 .............. 5,200 flight cycles or 

26,300 flight hours, 

whichever occurs first. 

1As of April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 

(75 FR 23572))). 2After April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 ((75 FR 11428, March 11, 2010; corrected May 4, 2010 

(75 FR 23572))). 3 ‘‘SR’’ applies to airplanes with average flights less than 4 flight hours. 

4 ‘‘LR’’ refers to airplanes with average flights of 4 or more flight hours. 

(2) For Model A300 and A300–600 

airplanes that have accumulated more than 

40,000 total flight hours as of April 15, 2010 

(the effective date of AD 2010–06–04, 

Amendment 39–16228 ((75 FR 11428, March 

11, 2010); corrected May 4, 2010 (75 FR 

23572))): Within 250 flight cycles after April 

15, 2010, do the actions specified in 

paragraph (g)(1) of this AD. 

(3) For Model A310 airplanes that have 

accumulated more than 55,500 total flight 

hours as of April 15, 2010 (the effective date 

of AD 2010–06–04, Amendment 39–16228 

((75 FR 11428, March 11, 2010); corrected 

May 4, 2010 (75 FR 23572))): Within 250 

flight cycles after April 15, 2010, do the 

actions specified in paragraph (g)(1) of this 

AD. 

(4) For Configuration 01 airplanes, as 

identified in the applicable service bulletin 

identified in paragraph (g)(9) of this AD: If a 

crack is found during any inspection 

required by paragraph (g)(1) of this AD, 

before further flight, install a doubler, in 

accordance with paragraph 3.C. of the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(9) of this AD. 

(5) For Configuration 02 airplanes, as 

identified in the applicable service bulletin 

identified in paragraph (g)(9) of this AD: At 

the applicable time specified in paragraph 

1.E.(2) of the applicable service bulletin 

identified in paragraphs (g)(9)(i) through 

(g)(9)(iii) of this AD, or within 250 flight 

cycles after April 15, 2010 (the effective date 

of AD 2010–06–04, Amendment 39–16228 

((75 FR 11428, March 11, 2010); corrected 

May 4, 2010 (75 FR 23572))), whichever 

occurs later, perform a detailed visual 

inspection of the pylons 1 and 2 side panels 

(upper section) at rib 8, in accordance with 

paragraph 3.B. of the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (g)(9) of this AD. 

(6) For Configuration 03 airplanes, as 

identified in the applicable service bulletin 

identified in paragraph (g)(9) of this AD: At 

the applicable time specified in paragraph 

1.E.(2) of the applicable service bulletin 

identified in paragraphs (g)(9)(i) through 

(g)(9)(iii) of this AD, or within 250 flight 

cycles after April 15, 2010 (the effective date 

of AD 2010–06–04, Amendment 39–16228 

((75 FR 11428, March 11, 2010); corrected 

May 4, 2010 (75 FR 23572))), whichever 

occurs later, perform a detailed visual 

inspection, and a high frequency eddy 

current inspection as applicable, of the 

pylons 1 and 2 side panels (upper section) at 

rib 8, in accordance with paragraph 3.B. of 

the Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(9) of this AD. 

(7) For Configuration 02 and 03 airplanes, 

as identified in the applicable service 

bulletin identified in paragraph (g)(9) of this 

AD: If a crack is found during any inspection 

required by paragraph (g)(1), (g)(5), or (g)(6) 

of this AD, before further flight, repair in 

accordance with paragraph 3.C. of the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(9) of this AD. 

(8) For all airplanes, except those in 

Configuration 01, as identified in the 

applicable service bulletin identified in 

paragraph (g)(9) of this AD: Repeat the 

inspection specified in paragraph (g)(1), 

(g)(5), or (g)(6) of this AD, as applicable, at 

the intervals specified in paragraph 1.E.(2) of 

the applicable service bulletin identified in 

paragraph (g)(9)(i) through (g)(9)(iii) of this 

AD. 

(9) For the actions specified in paragraph 

(g) of this AD, use the applicable service 

bulletin identified in paragraphs (g)(9)(i) 

through (g)(9)(iii) of this AD, or paragraph 

(k)(1), (k)(2), or (k)(3) of this AD. 

(i) Airbus Mandatory Service Bulletin 

A300–54–0075, excluding Appendixes 1, 2, 

and 3, Revision 02, dated June 26, 2008 (For 

Model A300 B2–1C, B2–203, B2K–3C, B4– 

103, B4–203, and B4–2C airplanes). 

(ii) Airbus Mandatory Service Bulletin 

A300–54–6015, excluding Appendixes 1, 2, 

and 3, Revision 02, dated June 26, 2008 (For 

Model A300 B4–601, B4–603, B4–605R, B4– 

620, B4–622, and B4–622R airplanes). 

(iii) Airbus Mandatory Service Bulletin 

A310–54–2018, excluding Appendixes 1, 2, 

and 3, Revision 02, dated June 26, 2008 (for 

Model A310 series airplanes). 

(h) New Repetitive Inspections and Repair 

Except as required by paragraphs (l)(1) and 

(l)(2) of this AD, at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

the applicable service bulletin identified in 

paragraph (k) of this AD: Do a detailed 

inspection for cracking of the pylons 1 and 


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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 81173 

2 side panels (upper section) at rib 8, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (k) of this AD. 

Accomplishing the inspection required by 

this paragraph terminates the requirements of 

paragraph (g)(1) through (g)(9) of this AD. 

(1) If any cracking is found, before further 

flight, do a high frequency eddy current 

(HFEC) inspection to confirm the crack, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (k) of this AD. 

(i) If any crack indication is confirmed 

during the HFEC inspection specified in 

paragraph (h)(1) of this AD, and the crack is 

less than 20 mm, before further flight, repair, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (k) of this AD. 

(ii) If any crack indication is confirmed 

during the HFEC inspection specified in 

paragraph (h)(1) of this AD and the crack is 

greater than or equal to 20 mm, 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) If no cracking is found, or if crack 

indication is not confirmed during the HFEC 

inspection required by paragraph (h)(1) of 

this AD, at the applicable interval specified 

in paragraph 1.E., ‘‘Compliance,’’ of the 

applicable service bulletin identified in 

paragraph (k) of this AD, repeat the 

inspection specified in paragraph (h) of this 

AD, in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (k) of this AD until 

the modification specified in paragraph (i) is 

done. 

(i) Optional Modification 

Modifying by installing a doubler on the 

left hand (LH) pylon 1 and right hand (RH) 

pylon 2, on pylon side panels (upper 

section), at rib 8, in accordance with the 

Accomplishment Instructions of the service 

information identified in paragraph (i)(1), 

(i)(2), or (i)(3) of this AD; as applicable; 

terminates the repetitive inspections 

specified in paragraph (h)(2) of this AD. 

(1) Airbus Service Bulletin A300–54–0081, 

dated August 11, 1993. 

(2) Airbus Service Bulletin A310–54–2024, 

dated August 11, 1993. 

(3) Airbus Service Bulletin A300–54–6021, 

Revision 02, dated May 21, 2008. 

(j) Post-Modification and Post-Repair 

Repetitive Inspections and Corrective 

Actions 

For airplanes on which the modification 

has been done as specified in paragraph (i) 

of this AD, and airplanes on which the repair 

has been done as specified in paragraph (h) 

of this AD: At the applicable compliance 

time specified in paragraph 1.E., 

Compliance,’’ of the applicable service 

bulletin identified in paragraph (k) of this 

AD, do the post-modification and post-repair 

detailed inspections for cracking, as 

applicable, of the LH and RH side panels of 

pylons 1 and 2, in accordance with the 

applicable service bulletins identified in 

paragraph (k) of this AD. Repeat the 

inspections thereafter at the times specified 

in paragraph 1.E., ‘‘Compliance’’ of the 

applicable service bulletin specified in 

paragraph (k) of this AD. If any cracking is 

found, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. This repair is not a 

terminating action for the repetitive 

inspections required by this paragraph. 

(k) New Service Information 

Use the applicable service bulletin 

identified in paragraphs (k)(1) through (k)(3) 

of this AD to accomplish the inspections 

required by paragraphs (g), (h), and (j) of this 

AD. 

(1) Airbus Service Bulletin A300–54–0075, 

Revision 03, excluding Appendixes 1, 2, 3, 

and 5; including Appendix 4; dated March 

27, 2013 (for Model A300 B2–1C, B2–203, 

B2K–3C, B4–103, B4–203, and B4–2C 

airplanes). 

(2) Airbus Service Bulletin A310–54–2018, 

Revision 03, excluding Appendixes 1, 2, 3, 

and 5; including Appendix 4; dated April 11, 

2013 (for Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes). 

(3) Airbus Service Bulletin A300–54–6015, 

Revision 03, excluding Appendixes 1, 2, 3, 

and 5; including Appendix 4; dated April 11, 

2013 (for Model A300 B4–601, B4–603, B4– 

605R, B4–620, B4–622, and B4–622R 

airplanes). 

(l) Exceptions 

(1) Where the compliance time column in 

the tables in paragraph 1.E., ‘‘Compliance,’’ 

of the applicable service bulletin identified 

in paragraph (k) of this AD specifies a 

‘‘threshold’’ in ‘‘FC’’ or ‘‘FH,’’ and does not 

specify from repair or service bulletin 

embodiment, those compliance times are 

total flight cycles and total flight hours. 

(2) Where the tables in paragraph 1.E., 

‘‘Compliance,’’ of the applicable service 

bulletin specified in paragraph (k) of this AD 

specifies ‘‘grace period after the receipt of the 

service bulletin,’’ this AD requires 

compliance within the corresponding 

compliance time after the effective date of 

this AD. 

(m) Credit for Previous Actions 

(1) This paragraph restates the credit 

provided by paragraph (f)(9) of AD 2010–06– 

04, Amendment 39–16228 ((75 FR 11428, 

March 11, 2010); corrected May 4, 2010 (75 

FR 23572)) with no changes. This paragraph 

provides credit for initial inspections 

required by paragraph (g) of this AD, if those 

actions were performed prior to April 15, 

2010 (the effective date of AD 2010–06–04) 

using the applicable service bulletins 

specified in paragraphs (m)(1)(i) through 

(m)(1)(vi) of this AD, which are not 

incorporated by reference in this AD. 

(i) Airbus Service Bulletin A300–54–0075, 

dated August 11, 1993. 

(ii) Airbus Service Bulletin A300–54–0075, 

Revision 01, dated November 9, 2007. 

(iii) Airbus Service Bulletin A300–54– 

6015, dated August 11, 1993. 

(iv) Airbus Service Bulletin A300–54– 

6015, Revision 01, dated November 9, 2007. 

(v) Airbus Service Bulletin A310–54–2018, 

dated August 11, 1993. 

(vi) Airbus Service Bulletin A310–54– 

2018, Revision 01, dated November 16, 2007. 

(2) This paragraph provides credit for 

initial inspections required by paragraph (h) 

of this AD, if those actions were performed 

before the effective date of this AD using the 

applicable service bulletins specified in 

paragraphs (m)(2)(i) through (m)(2)(ix) of this 

AD. 

(i) Airbus Service Bulletin A300–54–0075, 

dated August 11, 1993, which is not 

incorporated by reference in this AD. 

(ii) Airbus Service Bulletin A300–54–0075, 

Revision 01, dated November 9, 2007, which 

is not incorporated by reference in this AD. 

(iii) Airbus Service Bulletin A300–54– 

0075, Revision 02, dated June 26, 2008. 

(iv) Airbus Service Bulletin A300–54– 

6015, dated August 11, 1993, which is not 

incorporated by reference in this AD. 

(v) Airbus Service Bulletin A300–54–6015, 

Revision 01, dated November 9, 2007, which 

is not incorporated by reference in this AD. 

(vi) Airbus Service Bulletin A300–54– 

6015, Revision 02, dated June 26, 2008. 

(vii) Airbus Service Bulletin A310–54– 

2018, dated August 11, 1993, which is not 

incorporated by reference in this AD. 

(viii) Airbus Service Bulletin A310–54– 

2018, Revision 01, dated November 16, 2007, 

which is not incorporated by reference in this 

AD. 

(ix) Airbus Service Bulletin A310–54– 

2018, Revision 02, dated June 26, 2008. 

(3) This paragraph provides credit for 

initial inspections required by paragraph (i) 

of this AD, if those actions were performed 

before the effective date of this AD using the 

applicable service bulletins specified in 

paragraphs (m)(3)(i) and (m)(3)(ii) of this AD. 

(i) Airbus Service Bulletin A300–54–6021, 

dated August 11, 1993, which is not 

incorporated by reference in this AD. 

(ii) Airbus Service Bulletin A300–54–6021, 

Revision 01, dated November 16, 2007, 

which is not incorporated by reference in this 

AD. 

(n) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 


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81174 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 

of the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

2010–06–04, Amendment 39–16228 ((75 FR 

11428, March 11, 2010); corrected May 4, 

2010 (75 FR 23572)); are approved as AMOCs 

for the corresponding provisions of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0136R1, dated 

July 30, 2013, for related information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0648-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(5) and (p)(6) of this AD. 

(p) 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. 

(3) The following service information was 

approved for IBR on February 2, 2016. 

(i) Airbus Service Bulletin A300–54–0075, 

Revision 03, excluding Appendixes 1, 2, 3, 

and 5; including Appendix 4; dated March 

27, 2013. 

(ii) Airbus Service Bulletin A300–54–0081, 

dated August 11, 1993. 

(iii) Airbus Service Bulletin A300–54– 

6015, Revision 03, excluding Appendixes 1, 

2, 3, and 5; including Appendix 4; dated 

April 11, 2013. 

(iv) Airbus Service Bulletin A300–54– 

6021, Revision 02, dated May 21, 2008. 

(v) Airbus Service Bulletin A310–54–2018, 

Revision 03, excluding Appendixes 1, 2, 3, 

and 5; including Appendix 4; dated April 11, 

2013. 

(vi) Airbus Service Bulletin A310–54– 

2024, dated August 11, 1993. 

(4) The following service information was 

approved for IBR on April 15, 2010 ((75 FR 

11428, March 11, 2010); corrected May 4, 

2010 (75 FR 23572)). 

(i) Airbus Mandatory Service Bulletin 

A300–54–0075, excluding Appendixes 1, 2, 

and 3, Revision 02, dated June 26, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A300–54–6015, excluding Appendixes 1, 2, 

and 3, Revision 02, dated June 26, 2008. 

(iii) Airbus Mandatory Service Bulletin 

A310–54–2018, excluding Appendixes 1, 2, 

and 3, Revision 02, dated June 26, 2008. 

(5) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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

(6) 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. 

(7) 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 

December 8, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–31603 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–2015–0076; Directorate 

Identifier 2013–NM–246–AD; Amendment 

39–18350; AD 2015–26–02] 

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 all 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and Airbus Model A340–200, 

A340–300, A340–500, and A340–600 

series airplanes. This AD was prompted 

by a report that, during a production 

flight test, the ram air turbine (RAT) did 

not pressurize the green hydraulic 

system. For certain airplanes, this AD 

requires identification of the part 

number, serial number, and standard of 

the RAT pump, RAT module, RAT 

actuator, and RAT lower gearbox 

assembly; replacement of the balance 

weight screw, modification of the 

actuator coil spring, modification of the 

actuator, an inspection of the anti-stall 

valve for correct installation in the RAT 

pump housing; and corrective actions if 

necessary. For certain other airplanes, 

this AD requires re-identification or 

replacement of the RAT module. We are 

issuing this AD to prevent loss of the 

impeller function and RAT pump 

pressurization capability, which, if 

preceded by a total engine flame-out, 

could result in the loss of control of the 

airplane. 

DATES: This AD becomes effective 

February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 2, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0076; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For Airbus 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.A330A340@

airbus.com; Internet http://

www.airbus.com. For Hamilton 

Sundstrand service information 

identified in this AD, contact Hamilton 

Sundstrand, Technical Publications, 

Mail Stop 302–9, 4747 Harrison 

Avenue, P.O. Box 7002, Rockford, IL 

61125–7002; telephone 860–654–3575; 

fax 860–998–4564; email 

tech.solutions@hs.utc.com; Internet 

http://www.hamiltonsundstrand.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– 

0076. 

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 all Airbus Model A330–200, 

A330–200 Freighter, and A330–300 

series airplanes; and Airbus Model 

A340–200, A340–300, A340–500, and 

A340–600 series airplanes. The NPRM 


jstallworth on DSK7TPTVN1PROD with RULES