Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26115 

AMOC–REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0038, dated 

March 4, 2015, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2015–6539. 

(2) 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.airworth-eas@

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

You may view this service information at the 

FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

(n) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on April 20, 

2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10117 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2458; Directorate 

Identifier 2014–NM–122–AD; Amendment 

39–18468; AD 2016–07–23] 

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 A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by reports of in-flight loss of 

fixed and hinged main landing gear 

(MLG) fairings, and reports of postmodification MLG fixed fairing 

assemblies that have wear and 

corrosion. This AD requires, for certain 

airplanes, repetitive replacements of the 

fixed fairing upper and lower 

attachment studs of both left-hand (LH) 

and the right-hand (RH) MLG; and 

repetitive inspections for corrosion, 

wear, fatigue cracking, and loose studs 

of each forward stud assembly of the 

fixed fairing door upper and lower 

forward attachment of both LH and RH 

MLG; and replacement if necessary. 

This AD also provides an optional 

terminating modification for the 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs. We are issuing this AD to prevent 

in-flight detachment of an MLG fixed 

fairing and consequent damage to the 

airplane. 

DATES: This AD becomes effective June 

6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2458; 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, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

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

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 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– 

2458. 

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 by adding an AD that would 

apply to all Airbus Model A318, A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on July 8, 2015 (80 FR 38992) 

(‘‘the NPRM’’). The NPRM was 

prompted by reports of in-flight loss of 

fixed and hinged MLG fairings, and 

reports of post-modification MLG fixed 

fairing assemblies that have wear and 

corrosion. The NPRM proposed to 

require, for certain airplanes, repetitive 

replacements of the fixed fairing upper 

and lower attachment studs of both the 

LH and RH MLG; and repetitive 

inspections for corrosion, wear, fatigue 

cracking, and loose studs of each 

forward stud assembly of the fixed 

fairing door upper and lower forward 

attachment of both LH and RH MLG; 

and replacement if necessary. The 

NPRM also proposed an optional 

terminating modification for the 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs. We are issuing this AD to prevent 

in-flight detachment of an MLG fixed 

fairing and consequent damage to the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0001R1, dated January 

15, 2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A318, A319, A320, and A321 

series airplanes. The MCAI states: 

Several occurrences of in-flight loss of 

main landing gear (MLG) fixed and hinged 

fairings were reported. The majority of 

reported events occurred following 

scheduled maintenance activities. One result 

of the investigation was that a discrepancy 

between the drawing and the maintenance 

manuals was discovered. The maintenance 

documents were corrected to prevent misrigging of the MLG fixed and hinged fairings, 

which could induce fatigue cracking. 

Airbus issued Service Bulletin (SB) A320– 

52–1083, providing instructions for a onetime inspection of the MLG fixed fairing 

composite insert and the surrounding area, 

replacement of the adjustment studs at the 

lower forward position and adjustment to the 

new clearance tolerances. That SB was 

replaced by Airbus SB A320–52–1100 (mod 

27716) introducing a re-designed location 

stud, rod end and location plate at the 

forward upper and lower leg fixed-fairing 

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positions. Subsequently, reports were 

received of post-mod 27716/post-SB A320– 

52–1100 MLG fixed fairing assemblies with 

corrosion, which could also induce cracking. 

This condition, if not detected and 

corrected, could lead to further cases of inflight detachment of a MLG fixed fairing, 

possibly resulting in injury to persons on the 

ground and/or damage to the aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2014–0096 [http://

ad.easa.europa.eu/blob/easa_ad_2014_0096_

superseded.pdf/AD_2014–0096_1] to require 

[for certain airplanes] repetitive detailed 

inspections (DET) of the MLG fixed fairings, 

and, depending on findings, accomplishment 

of applicable corrective actions. That [EASA] 

AD also prohibited installation of certain 

MLG fixed fairing rod end assemblies and 

studs as replacement parts on aeroplanes 

incorporating Airbus mod 27716 in 

production, or modified in accordance with 

Airbus SB A320–52–1100 (any revision) in 

service. 

Since EASA AD 2014–0096 was issued, 

Airbus developed an alternative inspection 

programme to meet the AD requirements. In 

addition, a terminating action (mod 155648) 

was developed, which is to be made available 

for in service aeroplanes through Airbus SB 

A320–52–1165. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0096, which is superseded, and 

adds an optional terminating action for the 

repetitive inspections. For post-mod 

aeroplanes, i.e., incorporating Airbus mod 

155648 in production, or modified by Airbus 

SB A320–52–1165 in service, the only 

remaining requirement is to ensure that premod components are no longer installed. 

Prompted by these developments, EASA 

issued AD * * *, retaining the requirements 

of EASA AD 2014–0096, which was 

superseded, and adding an optional 

terminating action for the repetitive 

inspections. For post-mod aeroplanes, i.e., 

incorporating Airbus mod 155648 in 

production, or modified by Airbus SB A320– 

52–1165 in service, the only remaining 

requirement is to ensure that pre-mod 

components are no longer installed. 

Since that [EASA] AD was issued, it was 

discovered that a certain plate support, Part 

Number (P/N) D5285600620000 as listed in 

Table 3 of the [EASA] AD, remains part of 

the post SB A320–52–1165 configuration and 

is therefore not affected by any prohibition of 

installation—paragraph (11) of the [EASA] 

AD. In addition, an error was detected in 

Table 1 of the [EASA] AD (missing P/N plate 

support) and paragraph (9) was found to be 

incorrectly worded. 

For the reasons described above, this 

[EASA] AD is revised to introduce the 

necessary corrections. 

Required actions also include, for 

airplanes in Airbus pre-Airbus 

Modification 27716 and pre-Airbus 

Service Bulletin A320–52–1100 

configuration on which certain 

components have been installed, 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs of both the LH and RH MLG. An 

optional terminating modification also 

is provided for the repetitive 

replacements of the fixed fairing upper 

and lower attachment studs. 

The optional terminating modification 

includes a resonance frequency 

inspection for debonding of the 

composite insert and delamination of 

the honeycomb area around the insert, 

and applicable corrective actions if 

necessary; and installation of new studs, 

rod ends, and location plates at the 

forward upper and lower leg fixedfairing positions. 

An additional optional terminating 

modification, for airplanes in pre-Airbus 

Modification 27716 and pre-Airbus 

Service Bulletin A320–52–1100 

configuration, includes installation of a 

locking device, new studs, rod ends, 

and location plates at the forward upper 

and lower leg fixed-fairing positions. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2458. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Revise Applicability in 

SUMMARY Section of the NPRM 

United Airlines (UAL) requested that 

we revise the SUMMARY section of the 

NPRM to include Model A320 series 

airplanes. 

We agree with the commenter’s 

request. The published version of the 

NPRM SUMMARY inadvertently did not 

include Model A320 series airplanes. 

We have revised the SUMMARY section of 

this final rule accordingly. 

Request To Revise Inspection Findings 

UAL requested that we revise 

paragraphs (i), (k), and (m) of the 

proposed AD, by replacing the term 

‘‘fatigue’’ with ‘‘deformation.’’ UAL 

stated that the Accomplishment 

Instructions of Airbus Service Bulletin 

A320–52–1163, dated February 4, 2014, 

do not provide any specific method for 

doing a detailed inspection for 

indications of fatigue. 

We disagree with the commenter’s 

Request to replace the term ‘‘fatigue’’ 

with ‘‘deformation.’’ The intent of the 

Airbus service information and the FAA 

AD is to inspect for ‘‘fatigue cracking.’’ 

For clarity, we have revised the 

SUMMARY and Discussion sections of this 

final rule, and paragraphs (i), (k), and 

(m) of this AD, by changing ‘‘fatigue’’ to 

‘‘fatigue cracking.’’ 

Request To Use Revised Service 

Information 

American Airlines (AAL) requested 

that we revise the proposed AD to 

reference Airbus Service Bulletin A320– 

52–1163, Revision 01, including 

Appendix 01, dated June 22, 2015. 

We agree with the commenter’s 

request. No additional work is required 

by this revision of the service 

information. We have revised 

paragraphs (g), (i), (k), (l), and (m) of this 

AD to reference Airbus Service Bulletin 

A320–52–1163, Revision 01, including 

Appendix 01, dated June 22, 2015. We 

have added credit for the actions 

required by paragraphs (g), (i), (k), (l), 

and (m) of this AD, if those actions were 

performed before the effective date of 

this AD using Airbus Service Bulletin 

A320–52–1163, dated February 4, 2014. 

Request To Revise Re-Identification of 

Fairing Part Number 

AAL requested that we revise 

paragraphs (k), (l), (m), and (n) of the 

proposed AD to remove the reidentification of the fairing part number 

specified in Airbus Service Bulletin 

A320–52–1165, including Appendix 01, 

dated November 3, 2014, on airplanes 

that are pre-Airbus Modification 27716 

and post-modification Airbus Service 

Bulletin A320–52–1100. AAL stated that 

a discrepancy in Airbus Service Bulletin 

A320–52–1165, including Appendix 01, 

dated November 3, 2014, makes it 

impossible to re-identify the fairing part 

number. 

We agree with AAL that Airbus 

Service Bulletin A320–52–1165, 

including Appendix 01, dated 

November 3, 2014, has a discrepancy in 

the re-identification of the fairing part 

number. Airbus has revised the 

instructions for re-identification of the 

fairing part number for pre-Airbus 

Modification 27716 and postmodification Airbus Service Bulletin 

A320–52–1100 configuration airplanes 

in Airbus Service Bulletin A320–52– 

1165, Revision 01, dated October 23, 

2015, excluding Appendix 01, dated 

November 3, 2014, and including 

Appendix 02, dated October 23, 2015. 

We have revised paragraphs (k), (l)(1), 

(m), and (n)(3) of this AD to reference 

Airbus Service Bulletin A320–52–1165, 

Revision 01, dated October 23, 2015, 

excluding Appendix 01, dated 

November 3, 2014, and including 

Appendix 02, dated October 23, 2015, as 

the appropriate source of service 

information for the applicable actions in 

those paragraphs. 

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Request To Specify Allowable 

Corrosion Limits 

AAL requested that we specify the 

allowable corrosion limits that would 

allow release of the airplane into service 

with corroded stud assemblies. AAL 

stated that paragraph (l)(2) of the 

proposed AD allows an operator to 

release an airplane into service with 

corrosion on the stud assembly, without 

accomplishing any corrective action at 

the time of the corrosion findings, 

provided that the stud assembly is not 

loose. 

We disagree with the commenter’s 

request to specify corrosion limits in the 

AD. The corrosion level(s) and 

subsequent action(s) in general are 

defined in the AAL corrosion 

prevention and corrosion control 

maintenance program (CPCP). For this 

AD, operators have an option to either 

replace the affected stud assemblies 

(that have corrosion but the corroded 

stud is not loose) before further flight as 

specified in paragraph (l)(1) of this AD 

or perform repetitive inspections as 

specified in paragraph (l)(2) of this AD 

until corrective actions are done as 

specified in paragraph (m) of this AD. 

We have not changed this AD in this 

regard. 

Request to Add Paragraph To Specify 

No Reporting Is Required 

UAL requested that we add a 

paragraph in the proposed AD, to 

remove the Airbus Service Bulletin 

A320–52–1163, dated February 4, 2014, 

requirement to report all inspection 

findings to Airbus. 

We agree with the commenter’s 

request. We have added new paragraph 

(q) to this AD, which states that 

although Airbus Service Bulletin A320– 

52–1163, Revision 01, including 

Appendix 01, dated June 22, 2015, 

specifies to submit certain information 

to the manufacturer, and specifies that 

action as ‘‘RC’’ (Required for 

Compliance), this AD does not include 

that requirement. We have redesignated 

subsequent paragraphs accordingly. 

Although not required to do so by this 

AD, we recommend that operators 

submit such information based on the 

Airbus service information request. This 

information may be beneficial to Airbus 

for product improvements. 

Request To Clarify Repetitive 

Inspection Interval 

AAL requested clarification of the 

repetitive inspection interval in 

paragraph (l)(2) of the proposed AD. 

AAL stated that, if Airbus Service 

Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 

2015, was referenced in this AD, this 

service information includes an option 

for a repetitive inspection interval of 

750 flight cycles. 

We agree to clarify the repetitive 

inspection interval in paragraph (l)(2) of 

this AD. The 4-month repetitive 

inspection interval specified in 

paragraph (l)(2) of this AD has 

precedence over the 750-flight-cycle 

interval specified in Airbus Service 

Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 

2015. We have not changed this AD in 

this regard. 

Request To Revise Corrective Actions 

Delta Airlines (DAL) requested that 

we revise paragraph (k) of the proposed 

AD to require the replacement of only 

the affected assembly and not the upper 

and lower fixed fairing forward 

attachment assemblies of the LH and RH 

MLG because of one finding on an 

affected assembly. DAL stated that 

paragraph (k) of the proposed AD places 

an undue burden on operators by having 

to replace airworthy parts because one 

of the affected parts was found with a 

finding of corrosion, wear, fatigue 

cracking, or loose studs. 

We agree with the commenter’s 

request. We agree with DAL that only 

parts with indication of corrosion, wear, 

fatigue cracking, or loose studs should 

be replaced. We have revised paragraph 

(k) of this AD to require replacing 

discrepant upper and lower fixed fairing 

forward attachment stud assemblies of 

the LH and RH MLG. 

Request To Revise Exceptions to AD 

Actions 

DAL requested that we revise 

paragraph (o) of the proposed AD to 

indicate that paragraphs (g) through (n) 

of the proposed AD are not applicable 

to post-Airbus Modification 155648 

configuration airplanes. DAL stated that 

paragraph (o) of the proposed AD 

provides relief from the requirements of 

paragraphs (g) and (i) of the proposed 

AD, but related paragraphs (h), (j), (k), 

(l), and (n) of the proposed AD are not 

included in the relief. 

We agree with the commenter that the 

intent of this AD is to not require 

paragraphs (g) through (n) of this AD if 

conditions stated in paragraph (o) of this 

AD are met. The requirements of 

paragraphs (k), (l), and (m) of this AD 

are conditional and will not apply to 

operators that are not required to do 

paragraphs (g) and (i) of this AD. 

Paragraph (n) of this AD is an 

explanation of terminating actions. We 

have clarified paragraphs (h) and (j) of 

this AD to refer to the exempt airplanes. 

Request To Delete Paragraph (p)(1) of 

the Proposed AD, and Change Wording 

in Paragraphs (p)(1) Through (p)(4) of 

the Proposed AD 

DAL requested that we delete 

paragraph (p)(1) of the proposed AD. 

DAL stated that paragraph (p)(1) of the 

proposed AD applies to pre-Airbus 

Modification 27716 and pre-Airbus 

Service Bulletin A320–52–1100 

configuration airplanes, but provides a 

requirement for post-Airbus 

Modification 27716 or post-Airbus 

Service Bulletin A320–52–1100 

configuration airplanes, which is 

redundant with the requirements of 

paragraph (p)(2) of the proposed AD. 

Delta also requested that we replace the 

word ‘‘and’’ in paragraphs (p)(1) 

through (p)(4) of the proposed AD with 

‘‘or’’ to clarify the requirement and be 

consistent with the wording used in 

paragraph (i) of the proposed AD. 

We partially agree with the 

commenter’s requests. We agree with 

DAL to revise paragraphs (p)(1) through 

(p)(4) of this AD to replace ‘‘and’’ with 

‘‘or.’’ We do not agree with deleting 

paragraph (p)(1) of this AD. Paragraph 

(p)(1) of this AD is applicable for 

airplanes in pre-Airbus Modification 

27716 or pre-Airbus Service Bulletin 

A320–52–1100 configuration, and the 

parts prohibition is effective after doing 

the actions provided in paragraph (n)(2) 

of this AD. Paragraph (p)(2) of this AD 

is applicable for airplanes in postAirbus Modification 27716 or postAirbus Service Bulletin A320–52–1100 

configuration, and the parts prohibition 

is effective as of the effective date of this 

AD. Therefore, paragraphs (p)(1) and 

(p)(2) of this AD are not redundant. We 

have not changed this AD in this regard. 

Request To Delete Paragraph (p)(3) of 

the Proposed AD 

DAL requested that we delete 

paragraph (p)(3) of the proposed AD. 

DAL stated that paragraph (p)(3) of the 

proposed AD applies to pre-Airbus 

Modification 155648 and pre-Airbus 

Service Bulletin A320–52–1165 

configuration airplanes, but provides a 

requirement for post-Airbus 

Modification 155648 or post-Airbus 

Service Bulletin A320–52–1165, which 

is redundant with the requirements of 

paragraph (p)(4) of the proposed AD. 

We do not agree with the commenter’s 

request. Paragraph (p)(3) of this AD is 

applicable for airplanes which have not 

been modified to post-Airbus 

Modification 155648 or post-Airbus 

Service Bulletin A320–52–1165 

configuration. Paragraph (p)(4) of this 

AD is applicable for airplanes that are 

in post-Airbus Modification 155648 or 

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post-Airbus Service Bulletin A320–52– 

1165 configuration. We have not 

changed this AD in this regard. 

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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

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 

We reviewed the following service 

information: 

• Airbus Service Bulletin A320–52– 

1100, Revision 01, dated March 12, 

1999. This service information describes 

procedures for modification of the 

airplane to post-Airbus Modification 

27716 configuration (by replacing the 

location stud, rod end, and location 

plate at the forward upper and lower leg 

fixed-fairing positions of the MLG door 

assemblies). The modification includes 

a resonance frequency inspection for 

debonding of the composite insert and 

delamination of the honeycomb area 

around the insert, and applicable 

corrective actions. Corrective actions 

include repairing the insert. The actions 

in this service information are an 

optional terminating modification. 

• Airbus Service Bulletin A320–52– 

1163, Revision 01, including Appendix 

01, dated June 22, 2015. This service 

information describes procedures for 

inspection of the fixed fairing forward 

attachments of the MLG door 

assemblies, and replacement of the fixed 

fairing upper and lower attachment 

studs of the LH and RH MLG door 

assemblies. 

• Airbus Service Bulletin A320–52– 

1165, Revision 01, dated October 23, 

2015, excluding Appendix 01, dated 

November 3, 2014, and including 

Appendix 02, dated October 23, 2015. 

This service information describes 

procedures for replacing the fairing 

attachment stud assemblies of the MLG 

door assembly with new assemblies. 

The actions in this service information 

are an optional terminating 

modification. 

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. 

Explanation of ‘‘RC’’ (Required for 

Compliance) (RC) Procedures and Tests 

in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and helps to 

provide consistent judgment in AD 

compliance. The procedures and tests 

identified as RC in any service 

information have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the AD. 

However, procedures and tests that are 

not identified as RC are recommended. 

Those procedures and tests that are not 

identified as RC may be deviated from 

using accepted methods in accordance 

with the operator’s maintenance or 

inspection program without obtaining 

approval of an alternative method of 

compliance (AMOC), provided the 

procedures and tests identified as RC 

can be done and the airplane can be put 

back in an airworthy condition. Any 

substitutions or changes to procedures 

or tests identified as RC will require 

approval of an AMOC. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

We also estimate that it will take 

about 18 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $4,110 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$4,799,640, or $5,640 per product. 

We estimate that the optional 

terminating modification would take 

about 18 work-hours and require parts 

costing $4,110, for a cost of $5,640 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 18 work-hours and require parts 

costing $4,110, for a cost of $5,640 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

According to the manufacturer, some 

of the costs of this AD might be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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-2015-2458; or in 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26119 

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 adding 

the following new airworthiness 

directive (AD): 

2016–07–23 Airbus: Amendment 39–18468. 

Docket No. FAA–2015–2458; Directorate 

Identifier 2014–NM–122–AD. 

(a) Effective Date 

This AD becomes effective June 6, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by reports of inflight loss of fixed and hinged main landing 

gear (MLG) fairings, and reports of postmodification MLG fixed fairing assemblies 

that have wear and corrosion. We are issuing 

this AD to prevent in-flight detachment of an 

MLG fixed fairing and consequent damage to 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Replacements 

For airplanes in pre-Airbus Modification 

27716 and pre-Airbus Service Bulletin A320– 

52–1100 configuration, with any of the 

components installed that are identified in 

paragraphs (g)(1) through (g)(5) of this AD: At 

the applicable compliance time specified in 

paragraph (h) of this AD, replace fixed fairing 

upper and lower attachment studs of both 

left-hand (LH) and right-hand (RH) MLG, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015. Repeat the 

replacements thereafter at intervals not to 

exceed 6,500 flight cycles. 

(1) Plate—support having part number 

(P/N) D5284024820000. 

(2) Plate—support P/N D5284024820200. 

(3) Stud—adjustment having P/N 

D5284024420000. 

(4) Rod end assembly (lower) having P/N 

D5284000500000. 

(5) Rod end assembly (upper) having P/N 

D5284000600000. 

(h) Compliance Times for the Requirements 

of Paragraph (g) of This AD 

For airplanes identified in paragraph (g) of 

this AD, except as provided by paragraph (o) 

of this AD: Do the initial replacement 

required by paragraph (g) of this AD at the 

latest of the times specified in paragraphs 

(h)(1) through (h)(4) of this AD. 

(1) Before the accumulation of 6,500 total 

flight cycles since the airplane’s first flight. 

(2) Within 6,500 flight cycles since the last 

installation of a pre-Airbus Modification 

27716 stud on the airplane. 

(3) Within 1,500 flight cycles after the 

effective date of this AD. 

(4) Within 8 months after the effective date 

of this AD. 

(i) Repetitive Inspections 

For airplanes in post-Airbus Modification 

27716 or post-Airbus Service Bulletin A320– 

52–1100 configuration, with any of the 

components installed that are identified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD: 

At the applicable compliance time specified 

in paragraph (j) of this AD, do a detailed 

inspection of the LH and RH MLG forward 

stud assemblies of the fixed fairing door 

upper and lower forward attachments of both 

LH and RH MLG for indications of corrosion, 

wear, fatigue cracking, and loose studs, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015. Repeat the 

inspection thereafter at intervals not to 

exceed 12 months. Replacement of both LH 

and RH MLG forward stud assemblies on an 

airplane, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 2015, 

extends the interval for the next detailed 

inspection to 72 months; and the inspection 

must be repeated thereafter at intervals not to 

exceed 12 months. 

(1) Stud—adjustment having P/N 

D5285600720000. 

(2) Rod end assembly (lower) having P/N 

D5285600400000. 

(3) Rod end assembly (upper) having P/N 

D5285600500000. 

(j) Compliance Times for the Requirements 

of Paragraph (i) of This AD 

For airplanes identified in paragraph (i) of 

this AD, except as provided by paragraph (o) 

of this AD: Do the initial inspection required 

by paragraph (i) of this AD at the latest of the 

times specified in paragraphs (j)(1) through 

(j)(4) of this AD. 

(1) Before the accumulation of 72 months 

since the airplane’s first flight. 

(2) Within 72 months since the last 

installation of a post-Airbus Modification 

27716 assembly or since accomplishment of 

the actions specified in Airbus Service 

Bulletin A320–52–1100. 

(3) Within 1,500 flight cycles after the 

effective date of this AD. 

(4) Within 8 months after the effective date 

of this AD. 

(k) Corrective Action 

If any discrepancy (including any 

indication of corrosion, wear, fatigue 

cracking, or loose studs) of any MLG forward 

stud assembly is found during any inspection 

required by paragraph (i) of this AD, except 

as specified in paragraph (l) of this AD: 

Before further flight, replace the discrepant 

upper and lower fixed fairing forward stud 

assemblies of the LH and RH MLG, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015; or Airbus Service 

Bulletin A320–52–1165, Revision 01, dated 

October 23, 2015, excluding Appendix 01, 

dated November 3, 2014, and including 

Appendix 02, dated October 23, 2015. 

(l) Corrective Action or Repetitive 

Inspections for Certain Corrosion Findings 

If any corrosion is found during any 

inspection required by paragraph (i) of this 

AD on any MLG fixed fairing forward stud 

assembly (upper, lower, LH or RH), but the 

corroded stud is not loose: Do the action 

specified in paragraph (l)(1) or (l)(2) of this 

AD. 

(1) Before further flight, replace the 

affected assembly, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 2015; 

or Airbus Service Bulletin A320–52–1165, 

Revision 01, dated October 23, 2015, 

excluding Appendix 01, dated November 3, 

2014, and including Appendix 02, dated 

October 23, 2015. 

(2) Within 4 months after finding 

corrosion, and thereafter at intervals not to 

exceed 4 months, do a detailed inspection for 

indications of corrosion, wear, fatigue 

cracking, and loose studs of the forward stud 

assembly of the affected (LH or RH) MLG, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015. 

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26120 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

(m) Corrective Action for Inspections 

Specified in Paragraph (l)(2) of This AD 

If any indication of wear, fatigue cracking, 

or loose studs of any forward stud assembly 

is found during any inspection required by 

paragraph (l)(2) of this AD: Before further 

flight, replace the affected (LH or RH) MLG 

fixed fairing forward stud assembly, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015; or Airbus Service 

Bulletin A320–52–1165, Revision 01, dated 

October 23, 2015, excluding Appendix 01, 

dated November 3, 2014, and including 

Appendix 02, dated October 23, 2015. 

(n) Terminating Action 

(1) Replacement of parts on an airplane, as 

required by paragraph (g), (k), (l)(1), or (m) 

of this AD, does not constitute terminating 

action for the repetitive inspections required 

by paragraph (i) of this AD, except as 

specified in paragraph (n)(3) of this AD. 

(2) The repetitive replacements required by 

paragraph (g) of this AD may be terminated 

by modification of the airplane to postAirbus Modification 27716 configuration, 

including a resonance frequency inspection 

for debonding of the composite insert and 

delamination of the honeycomb area around 

the insert, and all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1100, Revision 01, 

dated March 12, 1999, provided all 

applicable corrective actions are done before 

further flight. Thereafter, refer to paragraph 

(i) of this AD to determine the compliance 

time for the next detailed inspection required 

by this AD. 

(3) Modification of an airplane, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1165, Revision 01, dated October 23, 

2015, excluding Appendix 01, dated 

November 3, 2014, and including Appendix 

02, dated October 23, 2015, constitutes 

terminating action for actions required by 

paragraphs (g) through (m) of this AD for the 

airplane on which the modification is done. 

(o) Exceptions to Certain AD Actions 

An airplane on which Airbus Modification 

155648 has been embodied in production is 

not affected by the requirements of 

paragraphs (g) and (i) of this AD, provided 

that no affected component, identified by 

part number as listed paragraphs (g)(1) 

through (g)(5) and (i)(1) through (i)(3) of this 

AD, has been installed on that airplane since 

first flight of the airplane. 

(p) Parts Installation Prohibition 

(1) For airplanes in pre-Airbus 

Modification 27716 or pre-Airbus Service 

Bulletin A320–52–1100 configuration: No 

person may install a component identified in 

paragraphs (g)(1) through (g)(5) of this AD on 

any airplane after doing the actions provided 

in paragraph (n)(2) of this AD. 

(2) For airplanes in post-Airbus 

Modification 27716 or post Airbus Service 

Bulletin A320–52–1100 configuration: As of 

the effective date of this AD, no person may 

install a component identified in paragraphs 

(g)(1) through (g)(5) of this AD on any 

airplane. 

(3) For airplanes in pre-Airbus 

Modification 155648 or pre-Airbus Service 

Bulletin A320–52–1165 configuration: No 

person may install a component identified in 

paragraphs (g)(1) through (g)(5) and (i)(1) 

through (i)(3) of this AD on any airplane after 

doing the actions provided in paragraph 

(n)(3) of this AD. 

(4) For airplanes in post-Airbus 

Modification 155648 or post-Airbus Service 

Bulletin A320–52–1165 configuration: As of 

the effective date of this AD, no person may 

install a component identified in (g)(1) 

through (g)(5) and (i)(1) through (i)(3) of this 

AD on any airplane. 

(q) No Reporting Requirement 

Although Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015, specifies to submit 

certain information to the manufacturer, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance), this AD does not include that 

requirement. 

(r) Credit for Previous Actions 

(1) This paragraph provides credit for 

optional actions provided by paragraph (n)(2) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–52–1100, 

dated December 7, 1998, which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

actions required by paragraphs (g), (i), (k), (l), 

and (m) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–52–1163, 

dated February 4, 2014, which is not 

incorporated by reference in this AD. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as specified in paragraph (q) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0001R1, dated 

January 15, 2015, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2015–2458. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(u) 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 A320–52–1100, 

Revision 01, dated March 12, 1999. 

(ii) Airbus Service Bulletin A320–52–1163, 

Revision 01, including Appendix 01, dated 

June 22, 2015. 

(iii) Airbus Service Bulletin A320–52– 

1165, Revision 01, dated October 23, 2015, 

excluding Appendix 01, dated November 3, 

2014, and including Appendix 02, dated 

October 23, 2015. 

(3) 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. 

(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. 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26121 

Issued in Renton, Washington, on April 13, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–09119 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3988; Directorate 

Identifier 2015–NM–005–AD; Amendment 

39–18491; AD 2016–08–15] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–17– 

51 for certain Bombardier, Inc. Model 

CL–600–2B16 airplanes. AD 2014–17– 

51 required inspecting the inboard flap 

fasteners of the hinge-box forward 

fitting at Wing Station (WS) 76.50 and 

WS 127.25 to determine the orientation 

and condition of the fasteners, as 

applicable, and replacement or 

repetitive inspections of the fasteners if 

necessary. AD 2014–17–51 also 

provided for optional terminating action 

for the requirements of that AD. This 

new AD requires accomplishment of the 

previously optional terminating action. 

This AD was prompted by a 

determination that that additional 

action is necessary. We are issuing this 

AD to detect and correct incorrectly 

oriented or fractured fasteners, that 

could result in premature failure of the 

fasteners attaching the inboard flap 

hinge-box forward fitting; failure of the 

fasteners could lead to the detachment 

of the flap hinge box and the flap 

surface, and consequent loss of control 

of the airplane. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 12, 2014 (79 FR 

64088, October 28, 2014). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 6, 2014 (79 FR 

9389, February 19, 2014). 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier, Inc., 400 Coˆte-Vertu 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. 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– 

3988. 

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– 

3988; 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 address for the 

Docket Office (telephone 800–647–5527) 

is 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 20590. 

FOR FURTHER INFORMATION CONTACT: Aziz 

Ahmed, Aerospace Engineer, Propulsion 

and Services Branch, ANE–173, FAA, 

New York Aircraft Certification Office 

(ACO), 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7329; fax 516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, 

October 28, 2014) (‘‘AD 2014–17–51’’). 

AD 2014–17–51 applied to certain 

Bombardier, Inc. Model CL–600–2B16 

airplanes. The NPRM published in the 

Federal Register on October 19, 2015 

(80 FR 63141) (‘‘the NPRM’’). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–27R1, 

dated August 29, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B16 airplanes. The MCAI states: 

There have been three in-service reports on 

604 Variant aeroplanes of a fractured fastener 

head on the inboard flap hinge-box forward 

fitting at Wing Station (WS) 76.50, found 

during a routine maintenance inspection. 

Investigation revealed that the installation of 

these fasteners on the inboard flap hinge-box 

forward fittings at WS 76.50 and WS 127.25, 

on both wings, does not conform to the 

engineering drawings. Incorrect installation 

may result in premature failure of the 

fasteners attaching the inboard flap hinge-box 

forward fitting. Failure of the fasteners could 

lead to the detachment of the flap hinge box 

and consequently the detachment of the flap 

surface. The loss of a flap surface could 

adversely affect the continued safe operation 

of the aeroplane. 

The original issue of [Canadian] AD CF– 

2013–39 [http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0054-0002] 

[which corresponds to FAA AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014)] mandated a detailed visual 

inspection (DVI) of each inboard flap hingebox forward fitting, on both wings, and 

rectification as required. Incorrectly oriented 

fasteners require repetitive inspections until 

the terminating action is accomplished. 

After the issuance of [Canadian] AD CF– 

2013–39, there has been one reported 

incident on a 604 Variant aeroplane where 

four fasteners were found fractured on the 

same flap hinge-box forward fitting. The 

investigation determined that the fasteners 

were incorrectly installed. 

The original issue of this [Canadian] AD 

was issued to reduce the initial and repetitive 

inspection intervals previously mandated in 

[Canadian] AD CF–2013–39, and to impose 

replacement of the incorrectly oriented 

fasteners within 24 months. The CL–600– 

1A11, –2A12 and –2B16 (601–3A/–3R 

Variant) aeroplanes are addressed through 

[Canadian] AD CF–2013–39R1. 

Revision 1 of this [Canadian] AD is issued 

to clarify the requirements for the initial and 

repetitive inspections. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3988. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Change to Paragraph (k) of This AD 

Paragraph (k) of the NPRM specified 

to do the replacement on ‘‘both’’ wings. 

However, the replacement only needs to 

be done on the affected wing on which 

incorrectly oriented fasteners were 

found but none were found to be 

fractured. We have revised paragraph (k) 

of this AD to specify accomplishing the 

replacement on the affected wings. We 

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