24200 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–16, dated 

June 11, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2015-0074-0003. 

(k) 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 Temporary Revision ALI– 

0472, dated February 27, 2014, to Section 1– 

32 of Part 2, Airworthiness Limitations, of 

the Bombardier CRJ Series Regional Jet 

Maintenance Requirements Manual, CSP B– 

053. 

(ii) Reserved. 

(3) For service information identified in 

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

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

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on April 14, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–09813 Filed 4–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0491; Directorate 

Identifier 2014–NM–023–AD; Amendment 

39–18130; AD 2015–07–02] 

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, Inc. Model CL–600–1A11 

(CL–600), CL–600–2A12 (CL–601), and 

CL–600–2B16 (CL–601–3A, CL–601–3R, 

and CL–604 Variants) airplanes. This 

AD was prompted by a determination 

that the forward lugs of the flap hinge 

box might not conform to engineering 

drawings, which could result in 

premature fatigue cracking. This AD 

requires revising the maintenance or 

inspection program to include new 

airworthiness limitations tasks; and 

measuring the forward lug edge distance 

of each flap hinge box, inspecting for 

cracking and damage (i.e., deformation 

or bearing failure) of the forward lug 

edge of each flap hinge box, and 

repairing any cracking or damage if 

necessary. We are issuing this AD to 

detect and correct non-conforming flap 

hinge box forward lugs, which could 

result in failure of the lugs and 

detachment of the flap hinge box and 

consequent detachment of the flap 

surface. 

DATES: This AD becomes effective June 

4, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 4, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0491 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 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–2014– 

0491. 

FOR FURTHER INFORMATION CONTACT: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7331; 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, Inc. Model 

CL–600–1A11 (CL–600), CL–600–2A12 

(CL–601), and CL–600–2B16 (CL–601– 

3A, CL–601–3R, and CL–604 Variants) 

airplanes. The NPRM published in the 

Federal Register on August 4, 2014 (79 

FR 45140). The NPRM was prompted by 

a determination that the forward lugs of 

the flap hinge box might not conform to 

engineering drawings, which could 

result in premature fatigue cracking. 

The NPRM proposed to require revising 

the maintenance or inspection program 

to include new airworthiness 

limitations tasks; and measuring the 

forward lug edge distance of each flap 

hinge box, inspecting for cracking and 

damage (i.e., deformation or bearing 

failure) of the forward lug edge of each 

flap hinge box, and repairing any 

cracking or damage if necessary. We are 

issuing this AD to detect and correct 

non-conforming flap hinge box forward 

lugs, which could result in failure of the 

lugs and detachment of the flap hinge 

box and consequent detachment of the 

flap surface. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–01, 

dated January 3, 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– 

600–1A11 (CL–600), CL–600–2A12 (CL– 

601), and CL–600–2B16 (CL–601–3A, 

CL–601–3R, and CL–604 Variants) 

airplanes. The MCAI states: 

The aeroplane manufacturer has 

determined that the flap hinge box forward 

lugs edge distance may not conform to the 

engineering drawings. Non-conforming flap 

hinge box forward lugs may result in 

premature fatigue cracking. 

Failure of the lugs 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. 

This [Canadian] AD mandates the 

incorporation of new Time Limits/

Maintenance Checks (TLMC) Airworthiness 

Limitations (AWL) tasks, and the 

measurement [and inspection for cracking 

and damage] of the forward lug edge distance 

of each flap hinge-box and rectification as 

required. 

Corrective actions include repairing 

damage and cracking. You may examine 

the MCAI in the AD docket on the 

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


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#!documentDetail;D=FAA-2014-0491- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 45140, 

August 4, 2014) and the FAA’s response 

to each comment. 

Request To Include Latest Revision of 

Service Information 

Bombardier, Inc. requested that we 

revise the NPRM (79 FR 45140, August 

4, 2014) to reflect the latest revisions of 

certain service information. 

We agree to include the latest 

revisions of certain service information. 

Bombardier has issued Service Bulletin 

604–57–007, Revision 01, dated 

November 12, 2014 (for Model CL–600– 

2B16 airplanes); and Service Bulletin 

605–57–005, Revision 01, dated 

November 12, 2014 (for Model CL–600– 

2B16 airplanes). This new service 

information does not add new work for 

the affected airplanes and was revised to 

update labor hours needed to perform 

the work and clarify work instructions. 

We have changed this AD to reference 

Bombardier Service Bulletin 604–57– 

007, Revision 01, dated November 12, 

2014; and Bombardier Service Bulletin 

605–57–005, Revision 01, dated 

November 12, 2014, throughout. We 

have also added a new paragraph (k) to 

this AD to give credit for actions 

performed before the effective date of 

this AD using Bombardier Service 

Bulletin 604–57–007, dated September 

26, 2013; and Bombardier Service 

Bulletin 605–57–005, dated September 

26, 2013. We redesignated subsequent 

paragraphs accordingly. 

Request To Correct Typographical 

Errors 

Bombardier, Inc., and an FAA 

airframe and powerplant mechanic 

noted typographical errors in Table 1 of 

the NPRM (79 FR 45140, August 4, 

2014) and requested they be corrected. 

We agree that there are typographical 

errors. We have revised table 1 to 

paragraph (g) of this AD. The temporary 

revision (TR) number has been corrected 

to read ‘‘5–275,’’ in certain rows of table 

1 to paragraph (g) of this AD, where in 

the NPRM (79 FR 45140, August 4, 

2014) the previous TR number read ‘‘5– 

276.’’ The revision of Bombardier CL– 

604 Time Limits/Maintenance Checks 

Manual, dated July 8, 2013, was 

corrected from revision ‘‘8’’ to revision 

‘‘20.’’ 

Explanation of Additional Change 

Made to This Final Rule 

We have removed Note 1 to paragraph 

(g) from this final rule. Instead, we have 

included that information in paragraph 

(g) of this AD. 

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 

45140, August 4, 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 45140, 

August 4, 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 the following 

service information. 

• Bombardier Service Bulletin 600– 

0762, dated September 26, 2013. This 

service information describes 

procedures for measuring the edge-toedge distance of the forward lugs for the 

flap hinge boxes and contacting the 

manufacturer for corrective actions for 

Bombardier, Inc. Model CL–600–1A11 

(CL–600) airplanes. 

Bombardier Service Bulletin 601– 

0631, dated September 26, 2013. This 

service information describes 

procedures for measuring the edge-toedge distance of the forward lugs for the 

flap hinge boxes and contacting the 

manufacturer for corrective actions for 

Bombardier, Inc. Model CL–600–2A12 

(CL–601 Variant) and CL–600–2B16 

(CL–601–3A and –3R Variant) airplanes. 

• Bombardier Service Bulletin 604– 

57–007, Revision 01, dated November 

12, 2014. This service information 

describes procedures for measuring the 

edge-to-edge distance of the forward 

lugs for the flap hinge boxes and 

contacting the manufacturer for 

corrective actions for Bombardier, Inc. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes having serial numbers (S/Ns) 

5301 through 5665 inclusive. 

• Bombardier Service Bulletin 605– 

57–005, Revision 01, dated November 

12, 2014. This service information 

describes procedures for measuring the 

edge-to-edge distance of the forward 

lugs for the flap hinge boxes and 

contacting the manufacturer for 

corrective actions for Bombardier, Inc. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes having S/Ns 5701 through 

5953 inclusive. 

• Canadair Challenger Temporary 

Revision 5–157, dated July 8, 2013, to 

Outboard Flap—Hinge Box Forward 

Lugs, to Canadair Challenger Time 

Limits/Maintenance Checks Manual, 

PSP 605. This service information 

describes an airworthiness limitations 

task and compliance times for 

inspecting the forward lugs of the 

outboard flap hinge box for Bombardier, 

Inc. Model CL–600–1A11 (CL–600) 

airplanes. 

Canadair Challenger Temporary 

Revision 5–158, Inboard Flap—Hinge 

Box Forward Lugs, dated July 8, 2013, 

to Canadair Challenger Time Limits/

Maintenance Checks Manual, PSP 605. 

This service information describes an 

airworthiness limitations task and 

compliance times for inspecting the 

forward lugs of the inboard flap hinge 

box for Bombardier, Inc. Model CL– 

600–1A11 (CL–600) airplanes. 

• Canadair Challenger Temporary 

Revision 5–262, Outboard and Inboard 

Flap—Hinge Box Forward Lugs, dated 

July 8, 2013, to Canadian Challenger 

Time Limits/Maintenance Checks 

Manual PSP 601. This service 

information describes airworthiness 

limitations tasks and compliance times 

for inspecting the forward lugs of the 

outboard and inboard flap hinge boxes 

for Bombardier, Inc. Model CL–600– 

2A12 (CL–601) airplanes. 

• Canadair Challenger Temporary 

Revision 5–275, Outboard Flap—Hinge 

Box Forward Lugs, dated July 8, 2013, 

to Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 

601A–5. This service information 

describes an airworthiness limitations 

task and compliance times for 

inspecting the forward lugs of the 

outboard flap hinge box for Bombardier, 

Inc. Model CL–600–2B16 (CL–601–3A 

Variants) airplanes. 

• Canadair Challenger Temporary 

Revision 5–276, Inboard Flap—Hinge 

Box Forward Lugs, dated July 8, 2013, 

to Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 

601A–5. This service information 

describes an airworthiness limitations 

task and compliance times for 

inspecting the forward lugs of the 

inboard flap hinge box for Bombardier, 

Inc. Model CL–600–2B16 (CL–601–3A 

and CL–601–3R Variant) airplanes. 

• Task 57–50–00–121, Special 

Detailed Inspection of the Forward Lugs 

of the Inboard Flap Hinge Box, of 

Section 5–10–30 of Part 2, 

‘‘Airworthiness Limitations,’’ of 


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Bombardier CL–605 Time Limits/

Maintenance Checks Manual, Revision 

8, dated July 8, 2013. This service 

information describes an airworthiness 

limitations task and compliance times 

for inspecting the forward lugs of the 

inboard flap hinge box for Bombardier, 

Inc. Model CL–600–2B16 (CL–604 

Variant) airplanes, having S/Ns 5701 

through 5953 inclusive. 

• Task 57–50–00–121, Special 

Detailed Inspection of the Forward Lugs 

of the Inboard Flap Hinge Box, of 

Section 5–10–30 of Part 2, 

‘‘Airworthiness Limitations,’’ of 

Bombardier CL–604 Time Limits/

Maintenance Checks Manual, Revision 

20, dated July 8, 2013. This service 

information describes an airworthiness 

limitations task and compliance times 

for inspecting the forward lugs of the 

inboard flap hinge box of Bombardier, 

Inc. Model CL–600–2B16 (CL–604 

Variant) airplanes, having S/Ns 5301 

through 5665 inclusive. 

• Task 57–52–01–102, Special 

Detailed Inspection of the Hinge—Box 

Forward Lugs of the Outboard Flap, of 

Section 5–10–30 of Part 2, 

‘‘Airworthiness Limitations,’’ of 

Bombardier CL–605 Time Limits/

Maintenance Checks Manual, Revision 

8, dated July 8, 2013. This service 

information describes an airworthiness 

limitations task and compliance times 

for inspecting the forward lugs of the 

outboard flap hinge box of Bombardier, 

Inc. Model CL–600–2B16 (CL–604 

Variant) airplanes, having S/Ns 5701 

through 5953 inclusive. 

• Task 57–52–01–102, Special 

Detailed Inspection of the Hinge—Box 

Forward Lugs of the Outboard Flap, of 

Section 5–10–30 of Part 2, 

‘‘Airworthiness Limitations,’’ of 

Bombardier CL–604 Time Limits/

Maintenance Checks Manual, Revision 

20, dated July 8, 2013. This service 

information describes an airworthiness 

limitations task and compliance times 

for inspecting the forward lugs of the 

outboard flap hinge box of Bombardier, 

Inc. Model CL–600–2B16 (CL–604 

Variant) airplanes, having S/Ns 5301 

through 5665 inclusive. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

Costs of Compliance 

We estimate that this AD affects 105 

airplanes of U.S. registry. 

We also estimate that it will take 

about 45 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $401,625, or $3,825 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the cost of parts or oncondition actions specified in this AD. 

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-2014-0491; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–07–02 Bombardier, Inc.: Amendment 

39–18130. Docket No. FAA–2014–0491; 

Directorate Identifier 2014–NM–023–AD. 

(a) Effective Date 

This AD becomes effective June 4, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(4) of this AD, 

certificated in any category. 

(1) Bombardier, Inc. Model CL–600–1A11 

(CL–600) airplanes, serial numbers 1004 

through 1085 inclusive. 

(2) Bombardier, Inc. Model CL–600–2A12 

(CL–601) airplanes, serial numbers 3001 

through 3066 inclusive. 

(3) Bombardier, Inc. Model CL–600–2B16 

(CL–601–3A and CL–601–3R Variants) 

airplanes, serial numbers 5001 through 5194 

inclusive. 

(4) Bombardier, Inc. Model CL–600–2B16 

(CL–604 Variants) airplanes, serial numbers 

5301 through 5665 inclusive, and 5701 

through 5953 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that the forward lugs of the flap hinge box 

might not conform to engineering drawings, 

which could result in premature fatigue 

cracking. We are issuing this AD to detect 

and correct non-conforming flap hinge box 

forward lugs, which could result in failure of 

the lugs and detachment of the flap hinge box 

and consequent detachment of the flap 

surface. 


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Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24203 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 60 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, by incorporating the 

applicable airworthiness limitation (AWL) 

tasks as specified in table 1 to this paragraph. 

The initial compliance time for doing the 

task is at the applicable times specified in 

table 1 to this paragraph. For the 

incorporation of tasks specified in the 

temporary revisions (TRs) specified in table 

1 to this paragraph of this AD that are a part 

of the maintenance or inspection program 

revision required by this paragraph, such 

incorporation may be done by inserting a 

copy of the applicable TRs specified in table 

1 to this paragraph into the applicable ‘‘time 

limits/maintenance checks’’ (TLMC) manuals 

specified in table 1 to this paragraph. When 

the applicable TRs specified in table 1 to this 

paragraph have been included in general 

revisions of the applicable TLMC manual 

specified in table 1 to this paragraph, the 

general revisions may be inserted in the 

applicable TLMC manual specified in table 1 

to this paragraph. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS

Affected airplanes Task No. Canadair service information Initial compliance time 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with inboard flaps having 

greater than 7,400 total flight cycles 

but equal to or less than 14,850 total 

flight cycles as of the effective date of 

this AD.

57–40–00–186 Canadair Challenger TR 5–158, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 605.

Within 500 flight cycles after the effective date of this AD, but not later 

than 15,100 total flight cycles. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with inboard flaps having 

greater than 14,850 total flight cycles 

as of the effective date of this AD.

57–40–00–186 Canadair Challenger TR 5–158, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 605.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with inboard flaps having 

equal to or less than 7,400 total flight 

cycles.

57–40–00–186 Canadair Challenger TR 5–158, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 605.

Before the accumulation of 7,900 total 

flight cycles. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with outboard flaps having 

greater than 7,500 total flight cycles, 

but equal to or less than 11,350 total 

flight cycles as of the effective date of 

this AD.

57–40–00–160 Canadair Challenger TR 5–157, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 605.

Within 500 flight cycles after the effective date of this AD, but no later than 

11,600 total flight cycles. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with outboard flaps having 

greater than 11,350 total flight cycles 

as of the effective date of this AD.

57–40–00–160 Canadair Challenger TR 5–157, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 605.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with outboard flaps having 

equal to or less than 7,500 total flight 

cycles.

57–40–00–160 Canadair Challenger TR 5–157, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 605.

Before the accumulation of 8,000 total 

flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with inboard flaps having 

greater than 7,400 total flight cycles, 

but equal to or less than 14,850 total 

flight cycles, as of the effective date 

of this AD.

57–40–01–101 Canadair Challenger TR 5–262, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601–5.

Within 500 flight cycles after the effective date of this AD, but no later than 

15,100 total flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with inboard flaps with 

greater than 14,850 total flight cycles 

as of the effective date of this AD.

57–40–01–101 Canadair Challenger TR 5–262, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601–5.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with inboard flaps with 

equal to or less than 7,400 total flight 

cycles as of the effective date of this 

AD.

57–40–01–101 Canadair Challenger TR 5–262, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601–5.

Before the accumulation of 7,900 total 

flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with outboard flaps with 

greater than 7,500 total flight cycles 

but equal to or less than 11,350 total 

flight cycles as of the effective date of 

this AD.

57–40–00–175 Canadair Challenger TR 5–262, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601–5.

Within 500 flight cycles after the effective date of this AD, but not later 

than 11,600 total flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with outboard flaps having 

greater than 11,350 total flight cycles 

as of the effective date of this AD.

57–40–00–175 Canadair Challenger TR 5–262, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601–5.

Within 250 flight cycles after the effective date of this AD. 


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24204 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS—Continued 

Affected airplanes Task No. Canadair service information Initial compliance time 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with outboard flaps having 

equal to or less than 7,500 total flight 

cycles as of the effective date of this 

AD.

57–40–00–175 Canadair Challenger TR 5–262, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601–5.

Before the accumulation of 8,000 total 

flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive with inboard flaps having greater than 7,400 

total flight cycles but equal to or less 

than 14,850 total flight cycles as of 

the effective date of this AD.

57–40–01–101 Canadair Challenger TR 5–276, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601A–5.

Within 500 flight cycles after the effective date of this AD, but not later 

than 15,100 total flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with inboard flaps having greater than 

14,850 total flight cycles as of the effective date of this AD.

57–40–01–101 Canadair Challenger TR 5–276, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601A–5.

Within 250 flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with inboard flaps having equal to or less 

than 7,400 total flight cycles as of the 

effective date of this AD.

57–40–01–101 Canadair Challenger TR 5–276, Inboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601A–5.

Before the accumulation of 7,900 total 

flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with 

outboard flaps having greater than 

7,500 total flight cycles but equal to 

or less than 11,350 total flight cycles 

as of the effective date of this AD.

57–40–00–174 Canadair Challenger TR 5–275, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601A–5.

Within 500 flight cycles after the effective date of this AD, but no later than 

11,600 total flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with 

outboard flaps having greater than 

11,350 total flight cycles as of the effective date of this AD.

57–40–00–174 Canadair Challenger TR 5–275, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601A–5.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with 

outboard flaps having equal to or less 

than 7,500 total flight cycles as of the 

effective date of this AD.

57–40–00–174 Canadair Challenger TR 5–275, Outboard Flap—Hinge Box Forward 

Lugs, dated July 8, 2013, of the 

Canadair Challenger TLMC Manual, 

PSP 601A–5.

Before the accumulation of 8,000 total 

flight cycles. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes having S/Ns 5301 through 

5665 inclusive, with inboard flaps.

57–50–00–121 Section 5–10–30, Special Detailed Inspection of the Forward Lugs of the 

Inboard Flap Hinge Box, of Part 2, 

Airworthiness Limitations, of Bombardier CL–604 TLMC Manual, Revision 20, dated July 8, 2013.

Before the accumulation of 7,800 total 

flight cycles, or within 500 flight cycles after the effective date of this 

AD, whichever occurs later. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes, S/Ns 5301 through 5665 

inclusive.

57–52–01–102 Section 5–10–30, Special Detailed Inspection of the Hinge—Box Forward 

Lugs of the Outboard Flap, of Part 2, 

Airworthiness Limitations, of Bombardier CL–604 TLMC Manual, Revision 20, dated July 8, 2013.

Before the accumulation of 7,800 total 

flight cycles, or within 500 flight cycles after the effective date of this 

AD, whichever occurs later. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes, S/Ns 5701 through 5953 

inclusive.

57–50–00–121 Section 5–10–30, Special Detailed Inspection of the Forward Lugs of the 

Inboard Flap Hinge Box, of Part 2, 

Airworthiness Limitations, of Bombardier CL–605 TLMC Manual, Revision 8, dated July 8, 2013.

Before the accumulation of 7,800 total 

flight cycles, or within 500 flight cycles after the effective date of this 

AD, whichever occurs later. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes, S/Ns 5701 through 5953 

inclusive.

57–52–01–102 Section 5–10–30, Special Detailed Inspection of the Hinge—Box Forward 

Lugs of the Outboard Flap, of Part 2, 

Airworthiness Limitations, of Bombardier CL–605 TLMC Manual, Revision 8, dated July 8, 2013.

Before the accumulation of 7,800 total 

flight cycles, or within 500 flight cycles after the effective date of this 

AD, whichever occurs later. 


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(h) Lug Edge Measurement and Inspection 

At the applicable times specified in table 

2 to this paragraph and paragraph (i)(1) of 

this AD, measure the forward lug edge 

distance of all flap hinge boxes, and do a 

general visual inspection for cracking and 

damage (i.e., deformation or bearing failure) 

of the forward lug edge of all flap hinge 

boxes, in accordance with the applicable 

service bulletin specified in table 2 to this 

paragraph and paragraph (i)(1) of this AD. 

TABLE 2 TO PARAGRAPHS (h) AND (i)(1) OF THIS AD—COMPLIANCE TIMES FOR LUG EDGE MEASUREMENT AND

INSPECTION

Airplane models Affected flaps Compliance time Service information 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Inboard flaps having less than or 

equal to 7,400 total flight cycles 

as of the effective date of this 

AD.

Before the accumulation of 7,900 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Inboard flaps having greater than 

7,400 total flight cycles, but 

equal to or less than 14,850 

total flight cycles as of the effective date of this AD.

Before the accumulation of 

15,100 total flight cycles, or 

within 500 flight cycles or 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Inboard flaps having greater than 

14,850 total flight cycles as of 

the effective date of this AD.

Within 250 flight cycles or 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Outboard flaps having equal to or 

less than 7,500 total flight cycles as of the effective date of 

this AD.

Before the accumulation of 8,000 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Outboard flaps having greater 

than 7,500 total flight cycles but 

less than or equal to 11,350 

total flight cycles as of the effective date of this AD.

Within 500 flight cycles or 48 

months after the effective date 

of this AD, whichever occurs 

first; but not exceeding 11,600 

total flight cycles.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Outboard flaps having greater 

than 11,350 total flight cycles 

as of the effective date of this 

AD.

Within 250 flight cycles or within 

48 months after the effective 

date of this AD, whichever occurs first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variants) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Inboard flaps having less than or 

equal to 7,400 total flight cycles 

as of the effective date of this 

AD.

Before the accumulation of 7,900 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Inboard flaps having greater than 

7,400 total flight cycles, but 

equal to or less than 14,850 

total flight cycles, as of the effective date of this AD.

Within 500 flight cycles or within 

48 months after the effective 

date of this AD, whichever occurs first; but not exceeding 

15,100 total flight cycles.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Inboard flaps having greater than 

14,850 total flight cycles as of 

the effective date of this AD.

Within 250 flight cycles or within 

48 months after the effective 

date of this AD, whichever occurs first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Outboard flaps having less than 

or equal to 7,500 total flight cycles as of the effective date of 

this AD.

Before the accumulation of 8,000 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Outboard flaps having greater 

than 7,500 total flight cycles, 

but equal to or less than 11,350 

total flight cycles, as of the effective date of this AD.

Within 500 flight cycles or within 

48 months after the effective 

date of this AD; but not exceeding 11,600 total flight cycles.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Outboard flaps having greater 

than 11,350 total flight cycles 

as of the effective date of this 

AD.

Within 250 flight cycles or 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 


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24206 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 

TABLE 2 TO PARAGRAPHS (h) AND (i)(1) OF THIS AD—COMPLIANCE TIMES FOR LUG EDGE MEASUREMENT AND

INSPECTION—Continued 

Airplane models Affected flaps Compliance time Service information 

Model CL–600–2B16 (CL–604 

Variant) airplanes having S/Ns 

5301 through 5665 inclusive.

Outboard and inboard flaps .......... Before the accumulation of 7,800 

total flight cycles or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 604– 

57–007, Revision 01, dated November 12, 2014. 

Model CL–600–2B16 (CL–604 

Variant) airplanes having S/Ns 

5701 through 5953 inclusive.

Outboard and inboard flaps .......... Before the accumulation of 7,800 

total flight cycles or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 605– 

57–005, Revision 01, dated November 12, 2014. 

(i) Corrective Actions 

(1) If, during the measurement required by 

paragraph (h) of this AD, the lug edge 

distance is equal to or greater than the limit 

specified in the applicable service bulletin 

specified in table 2 to paragraph (h) of this 

AD and this paragraph, no further action is 

required by this paragraph. 

(2) If, during the measurement required by 

paragraph (h) of this AD, the lug edge 

distance is below the limit specified in the 

applicable service bulletin specified in table 

2 to paragraphs (h) and (i)(1) of this AD, 

before further flight, repair 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. 

(3) If, during the inspection required by 

paragraph (h) of this AD, any cracking or 

damage is found, before further flight, repair 

using a method approved by the Manager, 

New York ACO, ANE–170, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO. If approved 

by the DAO, the approval must include the 

DAO-authorized signature. 

(j) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

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

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 604–57–007, dated 

September 26, 2013 (for Model CL–600–2B16 

airplanes); or Bombardier Service Bulletin 

605–57–005, dated September 26, 2013 (for 

Model CL–600–2B16 airplanes); which are 

not incorporated by reference in this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–01, dated 

January 3, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0491-0004. 

(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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 600–0762, 

dated September 26, 2013. 

(ii) Bombardier Service Bulletin 601–0631, 

dated September 26, 2013. 

(iii) Bombardier Service Bulletin 604–57– 

007, Revision 01, dated November 12, 2014. 

(iv) Bombardier Service Bulletin 605–57– 

005, Revision 01, dated November 12, 2014. 

(v) Canadair Challenger Temporary 

Revision 5–157, Outboard Flap—Hinge Box 

Forward Lugs, dated July 8, 2013, to Canadair 

Challenger Time Limits/Maintenance Checks 

Manual, PSP 605. 

(vi) Canadair Challenger Temporary 

Revision 5–158, Inboard Flap—Hinge Box 

Forward Lugs, dated July 8, 2013, to Canadair 

Challenger Time Limits/Maintenance Checks 

Manual, PSP 605. 

(vii) Canadair Challenger Temporary 

Revision 5–262, Outboard and Inboard 

Flap—Hinge Box Forward Lugs, dated July 8, 

2013, to Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 601. 

(viii) Canadair Challenger Temporary 

Revision 5–275, Outboard Flap—Hinge Box 

Forward Lugs, dated July 8, 2013, to 

Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 601A–5. 

(ix) Canadair Challenger Temporary 

Revision 5–276, Inboard Flap—Hinge Box 

Forward Lugs, dated July 8, 2013, to 

Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 601A–5. 

(x) Task 57–50–00–121 Special Detailed 

Inspection of the Forward Lugs of the 

Inboard Flap Hinge Box of Section 5–10–30 

of Part 2, ‘‘Airworthiness Limitations,’’ of 

Bombardier CL–605 Time Limits/

Maintenance Checks Manual, Revision 8, 

dated July 8, 2013. 

(xi) Task 57–50–00–121 Special Detailed 

Inspection of the Forward Lugs of the 

Inboard Flap Hinge Box of Section 5–10–30 

of Part 2, ‘‘Airworthiness Limitations,’’ of 

Bombardier CL–604 Time Limits/

Maintenance Checks Manual, Revision 20, 

dated July 8, 2013. 

(xii) Task 57–52–01–102 Special Detailed 

Inspection of the Hinge—Box Forward Lugs 

of the Outboard Flap of Section 5–10–30 of 

Part 2, ‘‘Airworthiness Limitations,’’ of 

Bombardier CL–605 Time Limits/

Maintenance Checks Manual, Revision 8, 

dated July 8, 2013. 

(xiii) Task 57–52–01–102 Special Detailed 

Inspection of the Hinge—Box Forward Lugs 

of the Outboard Flap of Section 5–10–30 of 

Part 2, ‘‘Airworthiness Limitations,’’ of 

Bombardier CL–604 Time Limits/

Maintenance Checks Manual, Revision 20, 

dated July 8, 2013. 

(3) For service information identified in 

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

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

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 


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(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on March 

25, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07802 Filed 4–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0589; Directorate 

Identifier 2014–NM–069–AD; Amendment 

39–18148; AD 2015–09–03] 

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 A318–111 and –112 

airplanes and Model A319, A320, and 

A321 series airplanes. This AD was 

prompted by reports of cracks on the 

forward corner fittings of engine pylon 

aft secondary structures. This AD 

requires repetitive inspections of certain 

forward corner fittings of the pylon aft 

secondary structures, and corrective 

actions if necessary. This AD also 

provides optional terminating action for 

the repetitive inspections. We are 

issuing this AD to detect and correct 

detachment of the lower fairing 

attachment and/or loss of the aft fixed 

fairing with the movable fairing from 

the airplane in flight, which could result 

in damage to the airplane. 

DATES: This AD becomes effective June 

4, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 4, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0589 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 No. 

FAA–2014–0589. 

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 certain Airbus Model A318– 

111 and –112 airplanes and Model 

A319, A320, and A321 series airplanes. 

The NPRM published in the Federal 

Register on September 3, 2014 (79 FR 

52267). The NPRM was prompted by 

reports of cracks on the forward corner 

fittings of engine pylon aft secondary 

structures. The NPRM proposed to 

require repetitive inspections of certain 

forward corner fittings of the pylon aft 

secondary structures, and corrective 

actions if necessary. The NPRM also 

proposed to provide optional 

terminating action for the repetitive 

inspections. We are issuing this AD to 

detect and correct detachment of the 

lower fairing attachment and/or loss of 

the aft fixed fairing with the movable 

fairing from the airplane in flight, which 

could result in 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 2014–0064, dated March 14, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition. The MCAI states: 

Several operators of A320 family 

aeroplanes have reported finding cracks on 

the forward corner fittings of engine pylon aft 

secondary structures, on the lateral face 

(lateral panel side). In some cases, these 

cracks had propagated onto the forward face 

(Rib 11 side). Investigation results have 

highlighted that these cracks are initiated by 

stress corrosion. 

This condition, if not detected and 

corrected, could lead to loss (i.e. detachment 

from the aeroplane) of the lower fairing 

attachment at Rib 10, and/or loss of the aft 

fixed fairing with the movable fairing, 

possibly resulting in * * * [damage to the 

airplane]. 

For the reasons described above, this 

[EASA] AD requires repetitive detailed 

inspections (DI) of the right hand (RH) Part 

Number (P/N) D54530014201 and left hand 

(LH) P/N D54530014200 corner fittings of 

engine pylon aft secondary structures (premod 38067 or pre-Airbus Service Bulletin 

(SB) A320–54–1019) to detect cracks or 

deformation in the splicing area with corner 

fitting between Ribs 11–12 and, depending 

on findings, replacement of the corner 

fittings. 

This [EASA] AD also recognizes that 

replacement of the corner fittings with 

improved parts (as per Airbus SB A320–54– 

1019) constitutes a terminating action for the 

repetitive DI required by this [EASA] AD. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0589- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 52267, 

September 3, 2014) and the FAA’s 

response to each comment. 

Requests to Reference Revised Service 

Bulletins 

United Airlines and US Airways 

requested that we revise the NPRM (79 

FR 52267, September 3, 2014) to 

reference Airbus Service Bulletin A320– 

54–1019, Revision 02, dated April 15, 

2014, in lieu of Airbus Service Bulletin 

A320–54–1019, Revision 01, dated April 

10, 2008. United Airlines also requested 

that we revise the NPRM to reference 

Airbus Service Bulletin A320–54–1022, 

Revision 03, dated April 15, 2014, in 

lieu of Airbus Service Bulletin A320– 

54–1022, Revision 02, dated July 12, 

2013. 

We agree with the commenters’ 

requests to reference revised service 

bulletins. Airbus Service Bulletin A320– 

54–1019, Revision 02, dated April 15, 

2014, improves the test procedures, and 

Airbus Service Bulletin A320–54–1022, 

Revision 03, dated April 15, 2014, 

specifies that certain actions in the 

Accomplishment Instructions are 


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