Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3313 

Issued in Fort Worth, Texas, on January 6, 

2016. 

Bruce E. Cain, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–00664 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0447; Directorate 

Identifier 2014–NM–019–AD; Amendment 

39–18368; AD 2016–01–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model DHC–8–400 series 

airplanes. This AD was prompted by a 

report of several cracks found on the 

forward passenger airstair door step 

assembly. This AD requires an 

inspection to determine the serial 

number of the airstair door step 

assembly, and if necessary, an electronic 

tap test, reidentification of the airstair 

door step assembly, and replacement of 

the airstair door step assembly. We are 

issuing this AD to detect and correct 

cracks in the forward passenger airstair 

door step assembly; such cracking could 

propagate and result in the structural 

failure of the steps and impede the 

evacuation of passengers in the event of 

an emergency egress situation. 

DATES: This AD becomes effective 

February 25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 25, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0447; 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 Bombardier, Inc., 

Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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– 

0447. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Zimmer, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7306; fax 

516–794–5531. 

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 Bombardier Model 

DHC–8–400 series airplanes. The NPRM 

published in the Federal Register on 

July 17, 2014 (79 FR 41661). The NPRM 

was prompted by a report of several 

cracks found on the forward passenger 

airstair door step assembly. The NPRM 

proposed to require an inspection to 

determine the serial number of the 

airstair door step assembly, and if 

necessary, an electronic tap test, 

reidentification of the airstair door step 

assembly, and replacement of the 

airstair door step assembly. We are 

issuing this AD to detect and correct 

cracks in the forward passenger airstair 

door step assembly; such cracking could 

propagate and result in the structural 

failure of the steps and impede the 

evacuation of passengers in the event of 

an emergency egress situation. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–20R1, 

dated December 30, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

There has been one in-service report of 

several cracks being found on the forward 

passenger airstair door step assembly 

between the steps and the sidewall panels. 

The investigation revealed that the 

application of potting compound may have 

been omitted during the bonding at the joint 

of the airstair door steps and the sidewalls. 

The omission of potting compound could 

cause the bonding sealant to crack. The 

cracks, if not detected, could propagate to 

result in the structural failure of the steps. 

In the event of an emergency egress 

situation, the failure of the airstair step 

assembly could impede the evacuation of 

passengers. 

This [Canadian] AD mandates the 

replacement of the affected forward 

passenger airstair step assembly with a new 

or reworked step assembly. 

Revision 1 of this [Canadian] AD provides 

additional instructions for performing an 

electronic tap test of the airstair step 

assembly if the Serial Number (S/N) of the 

airstair step assembly cannot be found. 

Required actions include an 

inspection to determine the serial 

number of the airstair door step 

assembly, and if necessary, an electronic 

tap test and reidentification and 

replacement of the assembly. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0447- 

0004. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 41661, 

July 17, 2014) and the FAA’s response 

to each comment. 

Request To Refer to Latest Service 

Information 

Republic Airlines and Horizon Air 

requested that we revise the NPRM (79 

FR 41661, July 17, 2014) to refer to the 

latest service information. 

We agree with the request. The 

revised service information, Bombardier 

Service Bulletin 84–52–77, Revision C, 

dated June 5, 2014, provides minor 

wording changes but does not change 

the procedures or add any airplanes. We 

have revised paragraphs (g) and (h) in 

this AD to refer to the new service 

information, and added Bombardier 

Service Bulletin 84–52–77, Revision B, 

dated October 31, 2013, to paragraph (i) 

of this AD, to provide credit for 

previous actions done before the 

effective date of this AD. 

Request To Allow Records Review 

Horizon Air requested that we revise 

paragraph (g) of the proposed AD (79 FR 

41661, July 17, 2014) to allow a review 

of aircraft records, in addition to a 

physical inspection, as a way to 

determine the serial number of the 

airstair door step assembly. 

We disagree with the request. A 

review of aircraft records may provide 

an appropriate means to determine 

serial numbers. For the airstair door step 

assembly, however, we understand that 

operators may remove and exchange the 


jstallworth on DSK7TPTVN1PROD with RULES
3314 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

assemblies within their fleet for repair, 

and replace them relatively quickly to 

minimize airplane downtime. In these 

cases, there may be a lag between the 

removal and replacement action and 

updating the records typically used to 

conduct a records review. In 

coordination with TCCA, we have 

determined that airplane records may 

not reliably reflect the serial numbers of 

all airstair door step assemblies present 

on the affected airplanes. However, 

under the provisions of paragraph (j)(1) 

of this AD, we will consider requests for 

approval of an alternative method of 

compliance for determining serial 

numbers, if sufficient data are submitted 

to substantiate that the new method 

would provide an acceptable level of 

safety. We have not changed this final 

rule regarding this issue. 

Request To Allow Maintenance Manual 

Tasks for Airstair Replacement 

Horizon Air requested that we revise 

paragraph (g)(1)(ii) of the proposed AD 

(79 FR 41661, July 17, 2014), which 

would conditionally require replacing 

the airstair door step assembly in 

accordance with Bombardier Service 

Bulletin 84–52–77, Revision B, dated 

October 31, 2013. For this action, 

Horizon Air requested that we also 

allow the replacement to be done using 

maintenance manual tasks 52–11–01– 

000–801 and 52–11–01–400–801. 

Horizon Air stated that the service 

information specified in the NPRM does 

not include any actions beyond those 

specified in the maintenance manual 

tasks. 

We disagree with the request. Part 3, 

‘‘Procedure,’’ of the Accomplishment 

Instructions of Bombardier Service 

Bulletin 84–52–77, Revision C, dated 

June 5, 2014, does, in fact, specify 

additional tasks not included in the 

maintenance manual tasks referenced by 

the commenter. The additional tasks 

include verification of the serial number 

of the new airstair door step assembly 

before installation, and adjustment and 

a functional check of the new door. We 

have not changed this AD regarding this 

issue. 

Request To Limit Requirements to Steps 

That Correct the Unsafe Condition 

Horizon Air requested that we revise 

the NPRM (79 FR 41661, July 17, 2014) 

to require only the section of the 

Accomplishment Instructions of 

Bombardier Service Bulletin 84–52–77, 

Revision C, dated June 5, 2014, that 

directly corrects the unsafe condition: 

paragraph 3.B., ‘‘Procedure.’’ Horizon 

Air stated that the unsafe condition is 

not directly corrected by 

accomplishment of the actions specified 

in paragraph 3.A., ‘‘Job Set-up,’’ and 

paragraph 3.C., ‘‘Close Out,’’ of the 

Accomplishment Instructions of 

Bombardier Service Bulletin 84–52–77, 

Revision C, dated June 5, 2014. Horizon 

Air added that incorporating the Job Setup and Close Out as a requirement of 

the AD would restrict an operator’s 

ability to perform other maintenance in 

conjunction with the incorporation of 

the service information. 

We agree with the request and the 

commenter’s rationale. We have revised 

paragraph (g) of this AD accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

41661, July 17, 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 41661, 

July 17, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Service 

Bulletin 84–52–77, Revision C, dated 

June 5, 2014, including Appendix A, 

and with the attached Short Brothers 

Service Bulletin D8400–52–0011, 

Revision C, dated February 26, 2014. 

The service information describes 

procedures for determining the airstair 

door step assembly serial number, doing 

an electronic tap test, and reidentifying 

and replacing the assembly. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by means identified in the 

ADDRESSES section of this AD. 

Costs of Compliance 

We estimate that this AD affects 76 

airplanes of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $6,460, or $85 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

up to 9 work-hours and require parts 

costing $206,175, for a cost of $206,940 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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-2014-0447; 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 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3315 

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 adding 

the following new airworthiness 

directive (AD): 

2016–01–09 Bombardier, Inc.: Amendment 

39–18368. Docket No. FAA–2014–0447; 

Directorate Identifier 2014–NM–019–AD. 

(a) Effective Date 

This AD becomes effective February 25, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

4001 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by a report of 

several cracks found on the forward 

passenger airstair door step assembly. We are 

issuing this AD to detect and correct cracks 

in the forward passenger airstair door step 

assembly, which could propagate and result 

in the structural failure of the steps and 

impede the evacuation of passengers in the 

event of an emergency egress situation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection, Electronic Tap Test, 

Reidentification, and Replacement of the 

Airstair Door Step Assembly 

For airplanes having serial numbers 4001 

through 4393: Within 320 days after the 

effective date of this AD, do an inspection to 

determine the serial number of the airstair 

door step assembly, in accordance with 

paragraph 3.B., ‘‘Procedure,’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–52–77, Revision C, dated 

June 5, 2014, including Appendix A, and 

with the attached Short Brothers Service 

Bulletin D8400–52–0011, Revision C, dated 

February 26, 2014. 

(1) If the serial number of the airstair door 

step assembly cannot be found, or if the 

serial number is illegible: Before further 

flight, do an electronic tap test to determine 

the existence of epoxy compound, in 

accordance with paragraph 3.B., 

‘‘Procedure,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–52–77, Revision C, dated June 5, 2014, 

including Appendix A, and with the attached 

Short Brothers Service Bulletin D8400–52– 

0011, Revision C, dated February 26, 2014. 

(i) If the existence of epoxy compound is 

confirmed, before further flight, reidentify 

the airstair door step assembly, in accordance 

with paragraph 3.B., ‘‘Procedure,’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–52–77, Revision C, dated 

June 5, 2014, including Appendix A, and 

with the attached Short Brothers Service 

Bulletin D8400–52–0011, Revision C, dated 

February 26, 2014. 

(ii) If the existence of epoxy compound is 

not confirmed: Within 6,000 flight hours after 

the effective date of this AD, replace the 

airstair door step assembly, in accordance 

with paragraph 3.B., ‘‘Procedure,’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–52–77, Revision C, dated 

June 5, 2014, including Appendix A, and 

with the attached Short Brothers Service 

Bulletin D8400–52–0011, Revision C, dated 

February 26, 2014. 

(2) If the serial number of the airstair door 

step assembly is in the affected range 

specified in paragraph 1.A., ‘‘Effectivity,’’ of 

Bombardier Service Bulletin 84–52–77, 

Revision C, dated June 5, 2014: Within 6,000 

flight hours after the effective date of this AD, 

replace the airstair door step assembly, in 

accordance with paragraph 3.B., 

‘‘Procedure,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–52–77, Revision C, dated June 5, 2014, 

including Appendix A, and with the attached 

Short Brothers Service Bulletin D8400–52– 

0011, Revision C, dated February 26, 2014. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install on any airplane an airstair 

door step assembly with part number 

85217008–001 containing a serial number in 

the affected range specified in paragraph 

1.A., ‘‘Effectivity,’’ of Bombardier Service 

Bulletin 84–52–77, Revision C, dated June 5, 

2014, including Appendix A, and with the 

attached Short Brothers Service Bulletin 

D8400–52–0011, Revision C, dated February 

26, 2014. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD if the 

serial number is known, and if those actions 

were performed before the effective date of 

this AD using Bombardier Service Bulletin 

84–52–77, Revision A, dated April 24, 2013; 

or Bombardier Service Bulletin 84–52–77, 

Revision B, dated October 31, 2013. This 

service information is not incorporated by 

reference in this AD. 

(j) 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 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: 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–20R1, 

dated December 30, 2013, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0447-0004. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(3) and (l)(5) of this AD. 

(l) 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) Bombardier Service Bulletin 84–52–77, 

Revision C, dated June 5, 2014, including 

Appendix A, which is undated, and attached 

Short Brothers Service Bulletin D8400–52– 

0011, Revision C, dated February 26, 2014. 

(ii) Reserved. 

(3) For Bombardier service information 

identified in this AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario M3K 

1Y5, Canada; telephone 416–375–4000; fax 

416–375–4539; email thd.qseries@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) For Short Brothers service information 

identified in this AD, contact Short Brothers 

PLC, Airworthiness, P.O. Box 241, Airport 

Road, Belfast, BT3 9DZ Northern Ireland; 


jstallworth on DSK7TPTVN1PROD with RULES
3316 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

telephone +44(0)2890–462469; fax 

+44(0)2890 468444; email 

michael.mulholland@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(5) 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. 

(6) 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 January 

4, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00378 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1422; Directorate 

Identifier 2014–NM–125–AD; Amendment 

39–18370; AD 2016–01–11] 

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) 98–18–26, 

for certain Airbus Model A320 series 

airplanes. AD 98–18–26 required 

repetitive inspections to detect fatigue 

cracking of the front spar vertical 

stringers on the wings; and repair, if 

necessary. This new AD requires 

repetitive high frequency eddy current 

(HFEC) inspections for cracking of the 

radius of the front spar vertical stringers 

and the horizontal floor beam on frame 

36, a rototest inspection for cracking of 

the fastener holes of the front spar 

vertical stringers on frame 36, and repair 

if necessary. This AD was prompted by 

reports that indicate new repetitive 

inspections having new thresholds and 

intervals are needed and that additional 

work is needed to accomplish the 

inspections on airplanes on which a 

previous modification has been 

accomplished. We are issuing this AD to 

detect and correct fatigue cracking of the 

front spar vertical stringers on the 

wings, which could result in the 

reduced structural integrity of the 

airframe. 

DATES: This AD becomes effective 

February 25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 25, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1422; 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, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

61 93 44 51; email account.airwortheas@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 

Number FAA–2015–1422. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998). AD 98–18–26 

applied to certain Airbus Model A320 

series airplanes. The NPRM published 

in the Federal Register on June 5, 2015 

(80 FR 32063). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0069, dated March 19, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Airbus 

Model A320–211, –212, and –231 

airplanes. The MCAI states: 

During center fuselage certification full 

scale fatigue test, cracks were found on the 

front vertical stringer at frame 36. Analysis of 

these findings indicated that a number of inservice aeroplanes could be similarly 

affected. 

This condition, if not detected and 

corrected, could lead to crack propagation 

and consequent deterioration of the 

structural integrity of the aeroplane. 

To address this potential unsafe condition, 

[Directorate General for Civil Aviation] 

DGAC France AD 97–311–105 [which 

corresponds to FAA AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998)] was issued to require 

repetitive [HFEC] inspections [for cracking] 

in accordance with the instruction of Airbus 

Service Bulletin (SB) A320–57–1016. At the 

same time, the modification provided by 

Airbus SB A320–57–1017 was considered to 

be terminating action for the repetitive 

inspections required by DGAC France AD 

97–311–105. 

Since that [DGAC] AD was issued, and 

following new analysis, modification per 

Airbus SB A320–57–1017 is no longer 

considered to be terminating action for the 

repetitive inspections as required by DGAC 

France AD 97–311–105. 

Aeroplanes with [manufacturer serial 

number] MSN 0080 up to 0155 inclusive 

have been delivered with the addition of a 5 

[millimeter] mm thick light alloy shim under 

the heads of 2 fasteners at the top end of the 

front spar vertical stringers (Airbus 

modification 21290P1546, which is the 

production line equivalent to in-service 

modification through Airbus SB A320–57– 

1017). From MSN 0156 and higher, all 

aeroplanes are delivered with vertical 

stiffeners of the forward wing spar upper end 

with stiffener cap thickness increased from 4 

to 6 mm (Airbus modification 21290P1547). 

Prompted by these findings, Airbus issued 

SB A320–57–1178 to introduce new 

repetitive inspections with new thresholds 

and intervals. 

For the reasons described above, DGAC 

France AD 97–311–105 is superseded and 

this [EASA] AD requires the repetitive 

inspections at new thresholds and intervals. 

After EASA issued [proposed 

airworthiness directive] PAD 14–021, it was 

discovered that additional work [HFEC 

inspections for cracking of the radius of spar 

vertical stringers and horizontal beam in the 

center fuselage of frame 36, and a rototest 

inspection for cracking of the fastener holes 

of the spar vertical stringers radius on Frame 

36 and repair if necessary], to be included in 

Revision 01 of Airbus SB A320–57–1178, is 

required to accomplish the inspections. This 

Final [EASA] AD has been amended 

accordingly. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1422- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 32063, 

June 5, 2015) and the FAA’s response to 

the comments. 


jstallworth on DSK7TPTVN1PROD with RULES