Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3297 

and cracks; and do all applicable corrective 

actions; in accordance with the instructions 

of paragraph 4.2.3.2 of Airbus AOT 

A71N010–15, dated September 30, 2015. Do 

all applicable corrective actions before 

further flight. 

(i) Parts Installation Limitation 

As of the effective date of this AD, 

installation of a CFM56–5A engine on an 

airplane is permitted, provided that the 

installation is accomplished using the torque 

values for forward engine mount bolts 

specified in paragraph 4.2.3.1 of Airbus AOT 

A71N010–15, dated September 30, 2015. 

Note 1 to paragraph (i) of this AD: 

Additional guidance for the re-torque can be 

found in Airbus A318/A319/A320/A321 

AMM, Task 71–00–00–400–040–A01, 

‘‘Installation of the Power Plant with Engine 

Positioner TWW 75E,’’ dated August 2015. 

(j) 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. 

(k) 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. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2015–0229, dated November 27, 2015, for 

related information. You may examine the 

MCAI on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–8433. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

(AOT) A71N010–15, dated September 30, 

2015. 

(ii) Reserved. 

(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.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on 

December 28, 2015. 

Phil Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–01110 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1987; Directorate 

Identifier 2014–NM–240–AD; Amendment 

39–18377; AD 2016–01–17] 

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–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes. This AD was prompted by 

reports of cracked forward door 

members of the inboard main landing 

gear (MLG) doors. This AD requires 

repetitive inspections of the inboard 

MLG doors, repairs if necessary, and 

replacement of the inboard MLG doors. 

This AD also provides optional 

terminating action for the door 

replacement. We are issuing this AD to 

prevent loss of an MLG door during 

flight, which could result in damage to 

the airplane. 

DATES: This AD becomes effective 

February 25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 25, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1987; 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–2015– 

1987. 

FOR FURTHER INFORMATION CONTACT: Aziz 

Ahmed, Aerospace Engineer, ANE–171, 

FAA, New York Aircraft Certification 

Office, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone 516–228– 

7329; 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–600–2C10 (Regional Jet Series 700, 

701, & 702) airplanes. The NPRM 

published in the Federal Register on 

June 30, 2015 (80 FR 37200). The NPRM 

was prompted by reports of cracked 

forward door members of the inboard 

MLG doors. The NPRM proposed to 

require repetitive inspections of the 

inboard MLG doors, repairs if necessary, 

and replacement of the inboard MLG 

doors. The NPRM also proposed 

optional terminating action for the door 

replacement. We are issuing this AD to 

prevent loss of an MLG door during 

flight, which could result in damage to 

the airplane. 


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Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–42, 

dated December 12, 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– 

600–2C10 (Regional Jet Series 700, 701, 

& 702) airplanes. The MCAI states: 

Cases of inboard MLG doors with cracked 

door forward members were found. A 

cracked inboard MLG door forward member 

could result in door departure from the 

aeroplane. Loss of an MLG door during flight 

could result in damage to the aeroplane and 

injury to persons on the ground. 

This [Canadian] AD mandates the 

repetitive inspection [and corrective actions 

if necessary] and replacement of the inboard 

MLG doors. 

The repetitive inspection is a detailed 

inspection for damage (including 

deformation, pulled or missing fasteners 

on the inner skins and outer skin, and 

cracks) on the inner skins, outer skin, 

and the forward member of the inboard 

MLG doors. Corrective actions include 

repairing, removing, or replacing the 

inboard MLG door. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!document

Detail;D=FAA-2015-1987-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (80 FR 37200, 

June 30, 2015) and the FAA’s response 

to the comment. 

Request To Revise Repair Instructions 

Envoy Airlines requested that we 

revise the wording in paragraph 

(i)(1)(ii)(A) of the proposed AD (80 FR 

37200, June 30, 2015) to clarify that 

removal of the MLG door is not required 

in all repair situations. Envoy Airlines 

stated that Bombardier Service Bulletin 

670BA–32–042, Revision A, dated July 

2, 2014, including Appendixes A and B, 

both dated November 5, 2013, specifies 

that repairs can be accomplished with 

the door installed in some situations. 

Envoy Airlines suggested that the text 

‘‘Repair and reinstall the door’’ in 

paragraph (i)(1)(ii)(A) of the proposed 

AD be reworded to specify ‘‘repair the 

door.’’ 

We agree with the commenter’s 

request to revise the repair instructions. 

We have revised paragraph (i)(1)(ii)(A) 

of this AD by removing the instructions 

to reinstall the door. 

Clarification of Actions 

We have clarified the inspection area 

in paragraph (g) of this AD by specifying 

to inspect for damage on the inner skins, 

outer skin, and the forward member of 

the inboard MLG doors. 

Paragraph (i)(1)(ii)(A) of the proposed 

AD (80 FR 37200, June 30, 2015) 

specifies to do a repair ‘‘if repair of the 

inboard MLG is possible.’’ We have 

revised paragraph (i)(1)(ii)(A) of this AD 

to clarify the repair is done if it is 

possible to repair the inboard MLG door 

in accordance with the Accomplishment 

Instructions of Bombardier Service 

Bulletin 670BA–32–042, Revision A, 

dated July 2, 2014, including 

Appendixes A and B, both dated 

November 5, 2013. 

We have also revised paragraph 

(i)(1)(i) of this AD to specify that clarify 

that removed damaged doors cannot be 

reinstalled, unless the door is repaired 

prior to reinstallation and the actions 

specified in paragraph (l) of this AD are 

done. 

We have also clarified the actions 

required by paragraphs (i)(1)(iii), (i)(2), 

(k)(1), and (k)(2)(i) of this AD by 

specifying that where Bombardier 

Service Bulletin 670BA–32–043, 

Revision A, dated November 13, 2014, 

specifies to contact the manufacturer for 

certain instructions, this AD requires 

accomplishing those actions using a 

method approved by the Manager, New 

York ACO, ANE–170, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO. 

We have also revised paragraph (m) of 

this AD to refer to the latest revision of 

Bombardier Service Bulletin 670BA–32– 

043, dated July 2, 2014. The ‘‘Pre SB 

Part Number’’ column of Section M, 

Relationship Chart, of Bombardier 

Service Bulletin 670BA–32–043, 

Revision A, dated November 13, 2014, 

is the same as that in Bombardier 

Service Bulletin 670BA–32–043, dated 

July 2, 2014. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 (80 FR 

37200, June 30, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 37200, 

June 30, 2015). 

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 Modification Summary 

Package IS670528200033, Revision A–2, 

dated October 11, 2005. This service 

information describes procedures for 

enlarging the forward and aft hinge 

cutouts of the MLG inboard and 

outboard doors. 

• Bombardier Service Bulletin 

670BA–32–040, Revision D, dated July 

2, 2014, including Appendix A, 

Revision A, dated July 2, 2014, and 

Appendix B, Revision B, dated July 2, 

2014. This service information describes 

procedures for increasing the clearances 

between the MLG fairing and the MLG 

doors. 

• Bombardier Service Bulletin 

670BA–32–040, Revision E, dated 

November 13, 2014, including 

Appendix A, Revision A, dated July 2, 

2014, and Appendix B, Revision B, 

dated July 2, 2014. This service 

information describes procedures for 

increasing the clearances between the 

MLG fairing and the MLG doors, and for 

enlarging the forward and aft hinge 

cutouts of the MLG inboard and 

outboard doors. 

• Bombardier Service Bulletin 

670BA–32–042, Revision A, dated July 

2, 2014, including Appendixes A and B, 

both dated November 5, 2013. This 

service information describes 

procedures for inspecting and repairing 

the inboard MLG door inner skins, outer 

skin, and the forward member. 

• Bombardier Service Bulletin 

670BA–32–043, dated July 2, 2014; and 

Bombardier Service Bulletin 670BA–32– 

043, Revision A, dated November 13, 

2014. This service information describes 

procedures for replacing the inboard 

MLG doors. 

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 of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 269 

airplanes of U.S. registry. 

We estimate that it will take about 16 

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 $31,000 

per product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $8,704,840, or $32,360 

per product. 


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In addition, we estimate that any 

necessary follow-on actions will take up 

to 44 work-hours and require parts 

costing up to $31,000, for a cost of up 

to $34,740 per product. We have no way 

of determining the number of aircraft 

that might need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1987; 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): 

2016–01–17 Bombardier, Inc.: Amendment 

39–18377; Docket No. FAA–2015–1987; 

Directorate Identifier 2014–NM–240–AD. 

(a) Effective Date 

This AD becomes effective February 25, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2C10 (Regional Jet Series 700, 701, 

& 702) airplanes, certificated in any category, 

serial numbers 10002 and subsequent, as 

identified in Bombardier Service Bulletin 

670BA–32–042, Revision A, dated July 2, 

2014, including Appendixes A and B, both 

dated November 5, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports of 

cracked forward door members of the inboard 

main landing gear (MLG) doors. We are 

issuing this AD to prevent loss of an MLG 

door during flight, which could result in 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Within 660 flight hours or 12 months after 

the effective date of this AD, whichever 

occurs first: Do a detailed inspection for 

damage (including deformation, pulled or 

missing fasteners on the inner skins and 

outer skin, and cracks) on the inner skins, 

outer skin, and the forward member of the 

inboard MLG doors, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–042, Revision A, 

dated July 2, 2014, including Appendixes A 

and B, both dated November 5, 2013. Repeat 

the inspection thereafter at intervals not to 

exceed 660 flight hours or 12 months, 

whichever occurs first. 

(h) Detailed Inspection Definition 

For the purposes of this AD, a detailed 

inspection is an intensive examination of a 

specific item, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 

intensity deemed appropriate. Inspection 

aids such as mirror, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate procedures may be required. 

(i) Corrective Actions 

(1) If any damage is found on any inner 

skin or outer skin of the inboard MLG door 

during any inspection required by paragraph 

(g) of this AD: Before further flight, do the 

actions specified in paragraph (i)(1)(i), 

(i)(1)(ii), or (i)(1)(iii) of this AD. 

(i) Remove the damaged inboard MLG 

door, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–042, Revision A, 

dated July 2, 2014, including Appendixes A 

and B, both dated November 5, 2013. A 

damaged inboard MLG door cannot be 

reinstalled, unless the repair specified in 

paragraph (i)(1)(ii) of this AD is done prior 

to reinstallation and the actions specified in 

paragraph (l) of this AD are done at the times 

specified in paragraph (l) of this AD. 

(ii) Repair the door as specified in 

paragraph (i)(1)(ii)(A) or (i)(1)(ii)(B) of this 

AD, as applicable. 

(A) If it is possible to repair the inboard 

MLG door in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–042, Revision A, 

dated July 2, 2014, including Appendixes A 

and B, both dated November 5, 2013: Repair 

the door, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–042, Revision A, 

dated July 2, 2014, including Appendixes A 

and B, both dated November 5, 2013. 

(B) If it is not possible to repair the inboard 

MLG door in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–042, Revision A, 

dated July 2, 2014, including Appendixes A 

and B, both dated November 5, 2013: Repair 

using a method approved by the Manager, 

New York Aircraft Certification Office (ACO), 

ANE–170, FAA; or Transport Canada Civil 

Aviation (TCCA); or Bombardier, Inc.’s TCCA 

Design Approval Organization (DAO). 

(iii) Replace the inboard MLG door, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–32–043, Revision A, dated November 

13, 2014, except, where Bombardier Service 

Bulletin 670BA–32–043, Revision A, dated 

November 13, 2014, specifies to contact the 

manufacturer for certain instructions, this AD 

requires accomplishing those actions using a 

method approved by the Manager, New York 

ACO, ANE–170, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO. 


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3300 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

(2) If any damage is found on the forward 

member of the inboard MLG door during any 

inspection required by paragraph (g) of this 

AD: Before further flight, replace the inboard 

MLG door, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–043, Revision A, 

dated November 13, 2014, except, where 

Bombardier Service Bulletin 670BA–32–043, 

Revision A, dated November 13, 2014, 

specifies to contact the manufacturer for 

certain instructions, this AD requires 

accomplishing those actions using a method 

approved by the Manager, New York ACO, 

ANE–170, FAA; or TCCA; or Bombardier, 

Inc.’s TCCA DAO. 

(j) Terminating Action 

Within 6,600 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first, except as provided by paragraph 

(l) of this AD: Replace the inboard MLG 

doors, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–043, Revision A, 

dated November 13, 2014; except, where 

Bombardier Service Bulletin 670BA–32–043, 

Revision A, dated November 13, 2014, 

specifies to contact the manufacturer for 

certain instructions, this AD requires 

accomplishing those actions using a method 

approved by the Manager, New York ACO, 

ANE–170, FAA; or TCCA; or Bombardier, 

Inc.’s TCCA DAO. 

(1) Doing the MLG door replacement 

required by the introductory text of 

paragraph (j) of this AD terminates the 

inspections required by paragraph (g) of this 

AD for that MLG door. 

(2) Doing the MLG door replacement 

required by the introductory text of 

paragraph (j) of this AD does not terminate 

the actions required by AD 2010–23–19, 

Amendment 39–16508 (75 FR 68695, 

November 9, 2010). 

(k) Optional Actions for Compliance With 

Paragraph (j) of This AD 

Doing any of the actions specified in 

paragraph (k)(1), (k)(2), (k)(3), or (k)(4) of this 

AD is acceptable for compliance with the 

requirements of paragraph (j) of this AD. 

(1) Replacement of the inboard MLG door, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–32–043, Revision A, dated November 

13, 2014, except, where Bombardier Service 

Bulletin 670BA–32–043, Revision A, dated 

November 13, 2014, specifies to contact the 

manufacturer for certain instructions, this AD 

requires accomplishing those actions using a 

method approved by the Manager, New York 

ACO, ANE–170, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO; and 

enlargement of the forward and aft hinge 

cutouts, in accordance with the procedures 

specified in Bombardier Modification 

Summary Package IS670528200033, Revision 

A–2, dated October 11, 2005. 

(2) Installation of an inboard MLG door 

assembly with a part number listed in the 

‘‘Post SB Part Number’’ column of Section M, 

Relationship Chart, of Bombardier Service 

Bulletin 670BA–32–043, dated July 2, 2014, 

in accordance with a method specified in 

paragraph (k)(2)(i) or (k)(2)(ii) of this AD. 

(i) Do the installation in accordance with 

the Accomplishment instructions of 

Bombardier Service Bulletin 670BA–32–043, 

dated July 2, 2014; or Bombardier Service 

Bulletin 670BA–32–043, Revision A dated 

November 13, 2014; except, where 

Bombardier Service Bulletin 670BA–32–043, 

Revision A, dated November 13, 2014, 

specifies to contact the manufacturer for 

certain instructions, this AD requires 

accomplishing those actions using a method 

approved by the Manager, New York ACO, 

ANE–170, FAA; or TCCA; or Bombardier, 

Inc.’s TCCA DAO. 

(ii) Do the installation using a method 

approved by the Manager, New York ACO, 

ANE–170, FAA; or TCCA; or Bombardier, 

Inc.’s TCCA DAO. 

(3) Doing the actions specified in ‘‘PART 

C—Installation of the Inboard MLG Door Part 

Number CC670–10520–15 and Increase of the 

Clearance Between the Left MLG InboardDoor and the MLG Fairing’’ and ‘‘PART D— 

Installation of the Inboard MLG Door Part 

Number CC670–10520–16 and Increase of the 

Clearance Between the Right MLG InboardDoor and the MLG Fairing’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–040, Revision E, 

dated November 13, 2014, including 

Appendix A, Revision A, dated July 2, 2014, 

and Appendix B, Revision B, dated July 2, 

2014. 

(4) Doing the actions specified in 

paragraphs (k)(4)(i) and (k)(4)(ii) of this AD. 

(i) Doing the actions specified in ‘‘PART 

C—Installation of the Inboard MLG Door Part 

Number CC670–10520–15 and Increase of the 

Clearance Between the Left MLG InboardDoor and the MLG Fairing’’ and ‘‘PART D— 

Installation of the Inboard MLG Door Part 

Number CC670–10520–16 and Increase of the 

Clearance Between the Right MLG InboardDoor and the MLG Fairing’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–040, Revision D, 

dated July 2, 2014, including Appendix A, 

Revision A, dated July 2, 2014, and 

Appendix B, Revision B, dated July 2, 2014. 

(ii) Enlargement of the forward and aft 

hinge cutouts specified in Bombardier 

Modification Summary Package 

IS670528200033, Revision A–2, dated 

October 11, 2005. 

(l) Optional Delay of MLG Door Replacement 

If an MLG door is removed, the 

replacement required by paragraph (j) of this 

AD can be delayed until the MLG door is 

reinstalled. When the removed MLG door is 

reinstalled, the actions required by paragraph 

(j) of this AD must be done at the time 

specified in paragraph (j) of this AD. 

(m) Parts Installation Prohibition 

Upon completion of the actions specified 

in paragraph (j) or (k) of this AD, no person 

may install an inboard MLG door assembly 

with a part number listed in the ‘‘Pre SB Part 

Number’’ column of Section M, Relationship 

Chart, of Bombardier Service Bulletin 

670BA–32–043, Revision A, dated November 

13, 2014; on any airplane. 

(n) 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, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO authorized signature. 

(o) 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. 

(p) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–42, dated 

December 12, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1987-0002. 

(q) 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 Modification Summary 

Package IS670528200033, Revision A–2, 

dated October 11, 2005. 

(ii) Bombardier Service Bulletin 670BA– 

32–040, Revision D, dated July 2, 2014, 

including Appendix A, Revision A, dated 

July 2, 2014, and Appendix B, Revision B, 

dated July 2, 2014. 

(iii) Bombardier Service Bulletin 670BA– 

32–040, Revision E, dated November 13, 

2014, including Appendix A, Revision A, 

dated July 2, 2014, and Appendix B, Revision 

B, dated July 2, 2014. 

(iv) Bombardier Service Bulletin 670BA– 

32–042, Revision A, dated July 2, 2014, 

including Appendixes A and B, both dated 

November 5, 2013. 

(v) Bombardier Service Bulletin 670BA– 

32–043, dated July 2, 2014. 

(vi) Bombardier Service Bulletin 670BA– 

32–043, Revision A, dated November 13, 

2014. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3301 

(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 January 

6, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00630 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1045; Directorate 

Identifier 2014–NM–031–AD; Amendment 

39–18372; AD 2016–01–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A310 and Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes; and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes). This AD was prompted by a 

report of skin disbonding and damage 

found on the composite side panel of 

the rudder, located between the rudder 

core and skin of a previously repaired 

area. This AD requires an inspection for 

disbonding or damage of certain 

rudders, and related investigative 

actions and corrective actions if 

necessary. We are issuing this AD to 

detect and correct disbonding and 

damage of the rudder, which could 

result in reduced structural integrity of 

the rudder and consequent reduced 

controllability of the airplane. 

DATES: This AD is effective February 25, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 25, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-1045; 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 SAS, 

Airworthiness Office—EAW, 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–2014– 

1045. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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 A310 and 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes) series 

airplanes. The NPRM published in the 

Federal Register on January 23, 2015 

(80 FR 3525). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0026, dated January 28, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A310 and Airbus Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes; and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). The 

MCAI states: 

A case of skin disbonding was reported on 

a composite side of a rudder installed on an 

A310 aeroplane. 

The investigation results revealed that this 

disbonding started from a skin panel area 

previously repaired in-service in accordance 

with the Structural Repair Manual (SRM). 

The initial damage has been identified as 

a disbonding between the core and the 

repaired area. This damage may not be 

visually detectable and likely propagates 

during normal operation due to the variation 

of pressure during ground-air-ground cycles. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder, possibly resulting in reduced 

control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time 

thermography inspection of each repaired 

rudder or rudder whose maintenance records 

are incomplete and, depending on findings, 

accomplishment of applicable corrective and 

follow-up actions. 

Related investigative actions include 

doing a pulse thermography inspection 

for disbonding or damage of the leftand right-hand rudder side shells; a core 

ventilation through the inner skin, an 

elasticity laminate checker or ultrasonic 

inspection around the identified repairs 

in the booster area, and around 

identified fluid ingress; and a Tap test 

inspection of the glass fiber reinforced 

plastic area to identify skin-to-core 

disbonding and on identified repairs. 

Corrective actions include repairing or 

replacing any disbonded or damaged 

rudder. 

Depending on configuration and 

inspection results, the repetitive 

inspection intervals are 750 or 1,000 

flight cycles, or 500 flight hours or 4 

months, whichever occurs later. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-1045- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 3525, 

January 23, 2015) and the FAA’s 

response to each comment. 

No Justification for Issuing NPRM (80 

FR 3525, January 23, 2015) 

FedEx stated that Airbus has not 

provided any data or analysis showing 

the de-validated SRM procedures in the 

proposed AD (80 FR 3525, January 23, 

2015) as inadequate. FedEx noted that 

one finding on a Model A310 airplane 

with skin disbonding and damage found 

on the composite side panel of the 


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