79466 Federal Register / Vol. 80, No. 245 / Tuesday, December 22, 2015 / Rules and Regulations 

inspections of cam latch 1 and cam latch 2 

for any cracks. 

(h) Repetitive MCD Post-Rigging Inspections 

and Corrective Actions 

At the applicable times specified in table 

2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 757–52A0091, 

Revision 1, dated December 19, 2014: Do 

general visual inspections for any broken or 

missing cam latches, latch pins, and latch pin 

cross bolts; a detailed inspection of the cam 

latches and latch pins for any cracks, or any 

gouges in critical areas; and an HFEC or 

magnetic particle inspection of cam latch 1 

and cam latch 2 for cracks; and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 757–52A0091, 

Revision 1, dated December 19, 2014; except 

as required by paragraph (j)(2) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable times specified in 

table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 757–52A0091, 

Revision 1, dated December 19, 2014. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an alloy steel bolt as a 

cross bolt through any latch pin fitting 

assembly in the lower sill of the MCD on any 

airplane. 

(j) Exceptions to Service Bulletin 

Specifications 

The following exceptions apply in this AD. 

(1) Where Boeing Alert Service Bulletin 

757–52A0091, Revision 1, dated December 

19, 2014, specifies a compliance time after 

the original issue date of that service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Alert Service Bulletin 

757–52A0091, Revision 1, dated December 

19, 2014, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

corresponding actions required by 

paragraphs (g) and (h) of this AD, if those 

actions were done before the effective date of 

this AD, using Boeing Alert Service Bulletin 

757–52A0091, dated March 9, 2010, which is 

not incorporated by reference in this AD. 

(l) 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 (m)(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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Kimberly DeVoe, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6495; fax: 425–917–6590; 

email: kimberly.devoe@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) 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) Boeing Alert Service Bulletin 757– 

52A0091, Revision 1, dated December 19, 

2014. 

(ii) Reserved. 

(3) For 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. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on 

November 25, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–30818 Filed 12–21–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2714; Directorate 

Identifier 2014–SW–052–AD; Amendment 

39–18349; AD 2015–26–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS332C1, AS332L1, 

AS332L2, EC225LP, AS–365N2, AS 365 

N3, EC 155B, and EC155B1 helicopters 

with an energy absorbing seat (seat). 

This AD requires inspecting for the 

presence of labels that prohibit stowing 

anything under the seat. If a label is 

missing or not clearly visible to each 

occupant, we require installing a label. 

This AD was prompted by the discovery 

that required labels had not been 

systematically installed. The actions of 

this AD are intended to prevent objects 

from being stowed under the seat as 

these objects could reduce the energyabsorbing function of the seat, resulting 

in injury to the seat occupants during an 

accident. 

DATES: This AD is effective January 26, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of January 26, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

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– 

2714; or in person at the Docket 

Operations Office 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 service 


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Federal Register / Vol. 80, No. 245 / Tuesday, December 22, 2015 / Rules and Regulations 79467 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 14, 2015, at 80 FR 40947, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Airbus Helicopters Model AS332C1, 

AS332L1, AS332L2, EC225LP, AS– 

365N2, AS 365 N3, EC 155B, and 

EC155B1 helicopters with certain 

energy absorbing seats. The NPRM 

proposed to require inspecting for the 

presence of labels that would prohibit 

stowing anything under the seat. If a 

label is missing or not clearly visible to 

each occupant, the NPRM proposed to 

require installing a label. The proposed 

requirements were intended to prevent 

objects from being stowed under the 

seat as these objects could reduce the 

energy-absorbing function of the seat, 

resulting in injury to the seat occupants 

during an accident. 

The NPRM was prompted by AD No. 

2014–0204, dated September 11, 2014, 

and corrected September 12, 2014, by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union, to correct an unsafe condition 

for Airbus Helicopters Model AS332C1, 

AS332L1, AS332L2, EC225LP, AS– 

365N2, AS 365 N3, EC 155B, and 

EC155B1 helicopters. EASA advises that 

during certification of an energy 

absorbing seat with a new part number, 

the labels that require keeping the space 

under the seat free of any object were 

not systematically installed. EASA 

states that this condition, if not 

corrected, could prompt occupants to 

stow objects under an energy absorbing 

seat, which would reduce the 

effectiveness of the seat and the 

occupants’ chance of surviving an 

accident. The EASA AD consequently 

requires a one-time inspection for the 

presence of labels and, if they are 

missing or unreadable, making and 

installing labels prohibiting the placing 

of an object under an energy absorbing 

seat. 

Since the NPRM was issued, the FAA 

Southwest Regional Office has relocated 

and a group email address has been 

established for requesting an FAA 

Alternative Methods of Compliance 

(AMOC) for a helicopter of foreign 

design. Therefore, we have revised the 

physical address throughout the AD and 

the email address for requesting an 

AMOC. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(80 FR 40947, July 14, 2015). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by France 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. 

Related Service Information Under 1 

CFR Part 51 

Airbus Helicopters issued Alert 

Service Bulletin (ASB) No. AS332– 

01.00.85 for Model AS332C1, AS332L1, 

and AS332L2 helicopters; ASB No. 

AS365–01.00.66 for Model AS–365N2 

and AS 365 N3 helicopters; ASB No. 

EC155–04A013 for EC 155B and 

EC155B1 helicopters; and ASB No. 

EC225–04A012 for Model EC225LP 

helicopters. All ASBs are Revision 0 and 

dated August 26, 2014. The ASBs state 

that during certification of an energy 

absorbing seat with a new part number, 

it was observed that the label, which 

indicates that the space under the seats 

must remain free of objects, was not 

systematically installed. Objects stowed 

under these seats reduce the energy 

absorbing function and thus jeopardize 

the occupant’s survival in the event of 

a crash, the ASBs state. Pending a 

definitive solution, Airbus Helicopters 

calls for affixing a label that states that 

nothing can be stored under the seats. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 52 

helicopters of U.S. Registry and that 

labor costs average $85 a work-hour. 

Based on these estimates, we expect that 

the inspection for the presence of a label 

takes a quarter work-hour for a labor 

cost of about $21. The cost of parts and 

time for installing a label are minimal, 

for a total cost of $21 per helicopter and 

$1,092 for the U.S. fleet. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 


rmajette on DSK2TPTVN1PROD with RULES
79468 Federal Register / Vol. 80, No. 245 / Tuesday, December 22, 2015 / Rules and Regulations 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–26–01 Airbus Helicopters: 

Amendment 39–18349; Docket No. 

FAA–2015–2714; Directorate Identifier 

2014–SW–052–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model AS332C1, AS332L1, AS332L2, 

EC225LP, AS–365N2, AS 365 N3, EC 155B, 

and EC155B1 helicopters with an energy 

absorbing seat (seat) listed in Figure 1 to 

paragraph (a) of this AD, certificated in any 

category. 

FIGURE 1 TO PARAGRAPH (a) 

Seat manufacturer Seat type Generic part 

No. 

Fischer + Entwicklungen ......................................................................................................................... H110 .............................. 9606-()-()-() 

H140 .............................. 0520-()-()-() 

H160 .............................. 0718-()-()-()-() 

185/410 .......................... 9507-()-()-() 

236/406 .......................... 9608-()-()-() 

SICMA Aero Seat or Zodiac Seats France ............................................................................................ Sicma 192 ...................... 192xx-xx-xx 

Sicma 159 ...................... 1591718-xx 

159110 

Socea Sogerma ...................................................................................................................................... ST102 ............................ 2510102-xx-xx 

ST107 ............................ 2010107-xx-xx 

ST120 ............................ 2520120-xx 

Note 1 to Figure 1 to paragraph (a) of this 

AD: ‘‘xx’’ can be any two alphanumeric 

characters and ‘‘()’’ can be any number of 

alphanumeric characters. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

object stowed under an energy absorbing 

seat. This condition could reduce the 

efficiency of the energy-absorbing function of 

the seat, resulting in injury to the seat 

occupants during an accident. 

(c) Effective Date 

This AD becomes effective January 26, 

2016. 

(d) 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. 

(e) Required Actions 

Within 110 hours time in service: 

(1) For Model AS332C1, AS332L1, 

AS332L2, and EC225LP helicopters: 

(i) Inspect the cabin and cockpit for labels, 

placards, or markings that prohibit stowing 

anything under the seats in the locations 

shown in the figure in the Appendix of 

Airbus Helicopters Alert Service Bulletin No. 

AS332–01.00.85 (ASB AS332–01.00.85) or 

No. EC225–04A012 (ASB EC225–04A012), 

both Revision 0 and dated August 26, 2014, 

as applicable for your model helicopter. 

(ii) If a label, placard, or marking is not 

located in every location depicted in the 

figure in the Appendix or is not visible and 

legible to every occupant, before further 

flight, install a placard in accordance with 

the Accomplishment Instructions, paragraph 

3.B., of ASB AS332–01.00.85 or ASB EC225– 

04A012, as applicable for your model 

helicopter. 

(2) For Model AS–365N2, AS 365 N3, EC 

155B, and EC155B1 helicopters: 

(i) Inspect each seat leg in the cabin and 

cockpit for labels, placards, or markings that 

prohibit stowing anything under the seats. 

(ii) If a label, placard, or marking does not 

exist on one leg of each seat or is not visible 

and legible, before further flight, install a 

placard in accordance with the 

Accomplishment Instructions, paragraph 

3.B., and the Appendix of Airbus Helicopters 

Alert Service Bulletin No. AS365–01.00.66 or 

No. EC155–04A013, both Revision 0 and 

dated August 26, 2014, as applicable for your 

model helicopter. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email email 9-ASW-FTW-AMOCRequests@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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0204, dated September 11, 2014, 

and corrected September 12, 2014. You 

may view the EASA AD on the Internet at 

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

FAA–2015–2714. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 1100, Placards and Markings. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Alert Service 

Bulletin No. AS332–01.00.85, Revision 0, 

dated August 26, 2014. 

(ii) Airbus Helicopters Alert Service 

Bulletin No. EC225–04A012, Revision 0, 

dated August 26, 2014. 

(iii) Airbus Helicopters Alert Service 

Bulletin No. AS365–01.00.66, Revision 0, 

dated August 26, 2014. 

(iv) Airbus Helicopters Alert Service 

Bulletin No. EC155–04A013, Revision 0, 

dated August 26, 2014. 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

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

641–3775; or at http://www.airbus

helicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

Room 6N–321, Fort Worth, TX 76177. 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 


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Federal Register / Vol. 80, No. 245 / Tuesday, December 22, 2015 / Rules and Regulations 79469 

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 December 

11, 2015. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–31849 Filed 12–21–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0675; Directorate 

Identifier 2014–NM–213–AD; Amendment 

39–18340; AD 2015–25–02] 

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 certain 

Airbus Model A330–200, –200 

Freighter, and –300 series airplanes; and 

all Airbus Model A340–200, –300, –500, 

and –600 series airplanes. This AD was 

prompted by reports of cracks at certain 

frames of the forward cargo door. This 

AD requires a detailed inspection for 

cracking of certain forward cargo doors, 

and repair if necessary. We are issuing 

this AD to detect and correct cracking at 

certain frames, which could result in the 

loss of structural integrity of the forward 

cargo door. 

DATES: This AD becomes effective 

January 26, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 26, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2015-0675; 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0675. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A330– 

200, –200 Freighter, and –300 series 

airplanes; and all Airbus Model A340– 

200, –300, –500, and –600 series 

airplanes. The NPRM published in the 

Federal Register on March 31, 2015 (80 

FR 17000). We are issuing this AD to 

detect and correct cracking at certain 

frames, which could result in the loss of 

structural integrity of the forward cargo 

door. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0228, dated October 20, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A330–200, –200 Freighter, and 

–300 series airplanes; and all Airbus 

Model A340–200, –300, –500, and –600 

series airplanes. The MCAI states: 

An A330 aeroplane operator reported 

recently cases of crack findings on two 

different aeroplanes, at frame 20A and at 

frame 20B close to beam 3 of the forward 

cargo door. The first finding was detected 

during scheduled maintenance, while the 

second one was found during an inspection 

prompted by the first finding. Subsequent 

analyses of these cracks identified that the 

first crack initiated at frame 20B, which is the 

first primary load path, leading to excessive 

loads at frame 20A and consequent cracking. 

Nevertheless, on the other aeroplane, a crack 

was detected on frame 20A only. Rupture of 

both frames 20A and 20B could lead to frame 

21 failure after a limited number of flight 

cycles (FC). 

This condition, if not detected and 

corrected, may potentially result in the loss 

of structural integrity of the forward cargo 

door, which could ultimately jeopardise the 

aeroplane’s safe flight. 

Prompted by these findings, Airbus issued 

Alert Operators Transmission (AOT) 

A52L010–14 to provide instructions for a 

one-time inspection of frames 20A, 20B and 

21 in the area of beam 3, until the half pitch 

between beam 2 and beam 3. 

For the reasons described above, this 

[EASA] AD requires identification of the Part 

Number (P/N) of the affected forward cargo 

doors, a one-time detailed inspection (DET) 

of each affected door and, depending on 

findings, accomplishment of applicable 

corrective action(s) [contacting Airbus]. 

This [EASA] AD is considered to be an 

interim action and further AD action may 

follow. 

Required actions also include sending 

inspection results to Airbus. You may 

examine the MCAI in the AD docket on 

the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2015- 

0675-0002. 

Correction for Service Information 

Typo 

On page 1 of Airbus AOT A52L010– 

14, dated September 30, 2014, at section 

‘‘2. Referenced Documentation,’’ ‘‘Ref. 

5’’ specifies page block ‘‘PB.801,’’ which 

is incorrect. This page block should be 

‘‘PB.401’’ instead. We have added new 

paragraph (k) to this AD to account for 

this correction, and have redesignated 

subsequent paragraphs. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 17000, 

March 31, 2015) and the FAA’s response 

to each comment. 

Request To Revise Part Number List 

Sequencing 

American Airlines (AA) requested 

that we revise the proposed AD (80 FR 

17000, March 31, 2015) by swapping the 

part numbers listed in paragraphs 

(g)(1)(ii) and (g)(1)(x) of the proposed 

AD to maintain alphanumeric order. 

American Airlines reasoned that the 

flow of the list is confusing. 

We agree to revise paragraphs (g)(1)(ii) 

and (g)(1)(x) of this AD for the reasons 

requested by American Airlines. 

Request for Justification 

AA asked whether a root cause has 

been determined that justifies the 

proposed inspection threshold. AA 

noted that paragraph (g)(1) of the 

proposed AD (80 FR 17000, March 31, 

2015) proposed that inspections on all 

affected doors be completed within 200 

flight cycles from the effective date of 

the AD. AA further noted from Airbus 

AOT A52L010–14, dated September 30, 


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