Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 49445 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A330–21–3154, 

Revision 01, dated April 10, 2013. 

(ii) Airbus Service Bulletin A340–21–4150, 

Revision 01, dated April 10, 2013. 

(iii) Airbus Service Bulletin A340–21– 

5044, Revision 01, dated April 10, 2013. 

(iv) Task 21.31.00/09, Remove Safety Valve 

for Restoration, of Section C–21, Air 

Conditioning, of Section C, Systems and 

Power-plant Section, of the Airbus A330 

Maintenance Review Board Report, Revision 

14, dated June 2013. 

(v) Task 21.31.00/09, Remove Safety Valve 

for Restoration, of Section C–21, Air 

Conditioning, of Section C, Systems and 

Power-plant Section, Airbus A340 

Maintenance Review Board Report, Revision 

14, dated June 2013. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

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

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

7, 2014. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19555 Filed 8–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0034; Directorate 

Identifier 2013–SW–006–AD; Amendment 

39–17948; AD 2014–16–24] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GbmH) (Airbus Helicopters) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–10– 

53 for Eurocopter Deutschland GmbH 

(ECD) (now Airbus Helicopters) Model 

EC135P1, EC135P2, EC135P2+, 

EC135T1, EC135T2, and EC135T2+ 

helicopters. AD 2012–10–53 required, 

before further flight and at specified 

intervals, checking and inspecting the 

upper and lower main rotor hub (MRH) 

shaft flanges for a crack, and inspecting 

the lower hub-shaft flange bolt 

attachment areas for a crack. Since we 

issued AD 2012–10–53, it has been 

determined that it is safe to increase the 

visual inspection intervals of the MRH 

shaft flanges from 10 hours time-inservice (TIS) to 50 hours TIS and 

remove the inspection of the lower MRH 

shaft flange bolt attachment areas. This 

new AD continues to require checking 

and inspecting the upper and lower 

MRH shaft flanges for a crack. These 

actions are intended to detect a crack on 

the MRH shaft flange, which if not 

corrected, could result in failure of the 

MRH and subsequent loss of control of 

the helicopter. 

DATES: This AD is effective September 

25, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 25, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, Texas 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http:// 

www.airbushelicopters.com/techpub. 

You may view this referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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–2014– 

0034; 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 European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference information, 

the economic evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 18, 2012, we issued 

Emergency AD 2012–10–53, which 

superseded Emergency AD 2012–10–51. 

Emergency AD 2012–10–53 was 

published in the Federal Register as a 

Final rule; request for comments on 

November 20, 2012, at 77 FR 69558. AD 

2012–10–53 required a repetitive pilot 

check of the lower MRH shaft flange for 

a crack, a repetitive inspection of the 

upper and lower MRH shaft flanges and 

bolt attachment areas for a crack, and 

replacing the MRH shaft if there is a 

crack. AD 2012–10–53 was prompted by 

three reported incidents of cracking on 

the lower hub-shaft flanges of EC135 

model helicopters. 

After we issued AD 2012–10–53, 

Eurocopter revised Alert Service 

Bulletin (ASB) No. EC135–62A–029, 

now at Revision 7, dated October 22, 

2012, which contains the procedures for 

the repetitive pilot checks and 

inspections. The inspection interval for 

the visual inspection of the MRH shaft 

flanges was increased to 50 flight hours 

based on results from full scale 

component testing. The note regarding 

the preflight check states that the time 

between two preflight checks must not 

exceed 6 flight hours, and clarifies that 

one flight may comprise of multiple 

take-offs and landings and a flight starts 

when the helicopter takes off and ends 

when the helicopter is on the ground 

with the engines shut off. Eurocopter 

also removed the visual inspection of 


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the blade bolt attachment areas from the 

ASB. 

EASA also revised its AD, now at 

EASA AD 2012–0085R5, dated October 

30, 2012, to correct this unsafe 

condition. EASA advises that based on 

results of the further full scale 

component testing, it has been 

determined that the interval for the 

repetitive visual inspections of the 

upper and lower hub shaft flanges can 

be extended to 50 flight hours. EASA 

AD No. 2012–0085R5 also references 

ECD ASB No. EC135–62A–029, Revision 

7, dated October 22, 2012, for related 

information. EASA considers AD 2012– 

0085R5 to be interim AD action and 

further AD action may follow. 

On January 16, 2014, we issued a 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to supersede 

AD 2012–10–53. The NPRM published 

in the Federal Register on January 31, 

2014 (79 FR 5325). The NPRM proposed 

to continue to require the repetitive 

visual pilot check and inspection of the 

upper and lower MRH shaft flanges, as 

well as the replacement requirements of 

AD 2012–10–53. An owner/operator 

(pilot) may perform the required visual 

check and must enter compliance with 

the applicable paragraph of the AD into 

the helicopter maintenance records in 

accordance with 14 CFR 43.9(a)(1) 

through (4) and 91.417(a)(2)(v). A pilot 

may perform this check because it 

involves only looking at the visible area 

of the MRH shaft flanges and can be 

performed equally well by a pilot or a 

mechanic. This check is an exception to 

our standard maintenance regulations. 

Further, the NPRM proposed to increase 

the repetitive visual inspection interval 

for MRH shafts with 400 hours or more 

TIS from 10 hours TIS to 50 hours TIS. 

Any alternative method of compliance 

(AMOC) previously approved in 

accordance with AD 2012–10–53 would 

continue to be considered approved as 

an AMOC for the corresponding 

requirements in this AD. 

Since we issued the NPRM, 

Eurocopter Deutschland GmbH changed 

its name to Airbus Helicopters 

Deutschland GmbH. This AD reflects 

that change and updates the contact 

information to obtain service 

documentation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (79 FR 5325, January 31, 2014). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA ADs. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed except for the name change 

previously described and a minor 

editorial change to meet current 

publishing requirements. The reference 

to ‘‘the applicability of this AD’’ in 

paragraph (f)(3) of this AD has been 

changed to reference ‘‘paragraph (a) of 

this AD.’’ These changes are consistent 

with the intent of the proposals in the 

NPRM (79 FR 5325, January 31, 2014) 

and will not increase the economic 

burden on any operator. 

Differences Between This AD and the 

EASA AD 

EASA considers its AD action to be an 

interim action; we do not consider this 

AD to be an interim AD action because 

the requirements for the applicable partnumbered MRH shafts are not expected 

to change. The EASA AD requires you 

to report the findings and send the 

removed MRH to ECD (now Airbus 

Helicopters), while this AD does not. 

The EASA AD requires the initial visual 

check within 3 days, while this AD 

requires the initial visual check before 

further flight. The EASA AD does not 

specify affected MRH shaft part 

numbers; this AD does because the FAA 

anticipates Airbus Helicopters will 

produce new part-numbered MRH 

shafts without the same unsafe 

condition. 

Related Service Information 

We reviewed Eurocopter ASB No. 

EC135–62A–029, Revision 7, dated 

October 22, 2012, which describes 

procedures for preflight checking the 

visible area of the upper and lower MRH 

shaft flanges and performing a repetitive 

visual inspection of the upper and lower 

MRH shaft for cracks. EASA classified 

this ASB as mandatory and issued AD 

No. 2012–0085R5 to ensure the 

continued airworthiness of these 

helicopters. 

Costs of Compliance 

We estimate that this AD affects 244 

helicopters of U.S. Registry. We estimate 

inspecting the MRH shaft flanges 

requires 2.5 work-hours at an average 

labor rate of $85 per work-hour, for a 

total cost per helicopter of $212 and a 

total cost to U.S. operators of $51,728 

per inspection cycle. Replacing an MRH 

shaft requires about 8 work-hours and 

required parts cost $55,715, for a total 

cost per helicopter of $56,395. 

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 have 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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


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Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 49447 

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) 

2012–10–53 (77 FR 69558, November 

20, 2012), and adding the following new 

AD: 

2014–16–24 Airbus Helicopters 

Deutschland GmbH (Previously 

Eurocopter Deutschland GmbH) 

Helicopters: Amendment 39–17948; 

Docket No. FAA–2014–0034; Directorate 

Identifier 2013–SW–006–AD. 

(a) Applicability 

This AD applies to Model EC135P1, 

EC135P2, EC135P2+, EC135T1, EC135T2, 

and EC135T2+ helicopters, with a main rotor 

hub (MRH) shaft, part number (P/N) 

L623M1006101, L623M1206101, 

L623M1006102, L623M1206102, 

L623M1006103, or L623M1206103 installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the MRH shaft flange, which could 

result in failure of the MRH and subsequent 

loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2012–10–53, 

Amendment 39–17254 (77 FR 69558, 

November 20, 2012). 

(d) Effective Date 

This AD becomes effective September 25, 

2014. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Before further flight, and thereafter at 

intervals not to exceed 6 hours time-inservice (TIS), check the MRH shaft lower 

flange and the visible area of the MRH shaft 

upper flange for a crack. Figures 1 and 2 to 

Paragraph (f)(1) of this AD are examples of 

cracks that have been discovered in the MRH 

shaft lower flange. The actions required by 

this paragraph may be performed by the 

owner/operator (pilot) holding at least a 

private pilot certificate, and must be entered 

into the aircraft records showing compliance 

with this AD in accordance with 14 CFR 43.9 

(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). 

The record must be maintained as required 

by 14 CFR 91.417, 121.380, or 135.439. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(2) For MRH shafts with 400 or more hours 

TIS, within 50 hours TIS, and thereafter at 

intervals not to exceed 50 hours TIS: 

(i) Remove the rotor-hub cap. 

(ii) Clean the upper and lower MRH shaft 

flange as depicted in Figure 2 of Eurocopter 

Alert Service Bulletin No. EC135–62A–029, 

Revision 7, dated October 22, 2012, and 

visually inspect for a crack. 

(3) If there is a crack in the upper or lower 

MRH shaft flange, before further flight, 

replace that MRH shaft with an airworthy 

MRH shaft. Replacing the MRH shaft with an 

MRH shaft having a P/N listed in paragraph 

(a) of this AD does not constitute terminating 

action for the requirements of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 


tkelley on DSK3SPTVN1PROD with RULESER21AU14.003</GPH>

Figure 1 to Paragraph (f)(l) 

Figure 2 to Paragraph (f)(l) 
Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 49449 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(3) Any AMOC approved previously in 

accordance with AD No. 2012–10–53, 

Amendment 39–17254 (77 FR 69558, 

November 20, 2012), is approved as an 

AMOC for the corresponding requirements in 

paragraph (f) of this AD. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2012–0085R5, dated October 30, 2012. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2014–0034. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220, Main Rotor Head. 

(j) 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 the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin No. 

EC135–62A–029, Revision 7, dated October 

22, 2012, excluding Figure 1. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, Texas 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://www.airbushelicopters 

.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on August 8, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19525 Filed 8–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0060; Directorate 

Identifier 2012–NM–194–AD; Amendment 

39–17943; AD 2014–16–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directives (AD) 2006–21– 

08, AD 2007–14–01, AD 2008–25–02, 

AD 2010–04–09, AD 2011–01–02, and 

AD 2012–16–05, for certain Airbus 

Model A330 and A340 series airplanes. 

AD 2006–21–08, AD 2007–14–01, AD 

2008–25–02, AD 2010–04–09, AD 2011– 

01–02, and AD 2012–16–05 required 

revising the maintenance program or 

inspection program to incorporate 

certain maintenance requirements and 

airworthiness limitations for fuel tank 

systems. This new AD requires a new 

maintenance or inspection program 

revision. This AD was prompted by a 

determination that more restrictive 

maintenance requirements and 

airworthiness limitations are necessary. 

We are issuing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD becomes effective 

September 25, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 25, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0060; 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 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. 

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 to supersede the ADs listed 

below: 

• Airworthiness Directive AD 2006– 

21–08, Amendment 39–14793 (71 FR 

61639, October 19, 2006); 

• AD 2007–14–01, Amendment 39– 

15123 (72 FR 38006, July 12, 2007); 

• AD 2008–25–02, Amendment 39– 

15760 (73 FR 75307, December 11, 

2008); 

• AD 2010–04–09, Amendment 39– 

16202 (75 FR 7940, February 23, 2010; 

corrected March 3, 2010 (75 FR 9515)); 

• AD 2011–01–02, Amendment 39– 

16555 (76 FR 432, January 5, 2011); and 

• AD 2012–16–05, Amendment 39– 

17152 (77 FR 48425, August 14, 2012). 

Airworthiness Directives AD 2006– 

21–08, AD 2007–14–01, AD 2008–25– 

02, AD 2010–04–09, AD 2011–01–02, 

and AD 2012–16–05 applied to certain 

Airbus Model A330 and A340 series 

airplanes. The NPRM published in the 

Federal Register on February 27, 2014 

(79 FR 11019). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0168, 

dated August 31, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

certain Airbus Model A330 and A340 

series airplanes. The MCAI states: 

Prompted by an accident [involving a fuel 

tank system explosion in flight] * * * the 

FAA published Special Federal Aviation 

Regulation (SFAR) 88 (66 FR 23086, May 7, 

2001) and the Joint Aviation Authorities 

(JAA) published Interim Policy INT/POL/25/ 

12. The design review conducted Airbus to 

develop Fuel Airworthiness Limitations 

(FAL) for Airbus on A330 and A340 

aeroplanes in response to these regulations. 

The FAL* * * have been approved by the 

European Aviation Safety Agency 

(EASA)* * *ALS Part 5. 

Failure to comply with items as identified 

in Airbus A330 and A340 ALS Part 5 could 

result in a fuel tank explosion and 

consequent loss of the aeroplane. 

To address this condition, EASA issued: 


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