Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 81165 

(u) Small bank—(1) Definition. Small 

bank means a bank that, as of December 

31 of either of the prior two calendar 

years, had assets of less than $1.216 

billion. Intermediate small bank means 

a small bank with assets of at least $304 

million as of December 31 of both of the 

prior two calendar years and less than 

$1.216 billion as of December 31 of 

either of the prior two calendar years. 

* * * * * 

§ 345.42 [Amended] 

■ 15. Section 345.42 is amended: 

■ a. In paragraphs (b)(3) and (d), by 

removing ‘‘part 203’’ and adding ‘‘part 

1003’’ in its place, wherever it appears; 

and 

■ b. In paragraph (i), by removing ‘‘, the 

Office of the Comptroller of the 

Currency, and the Office of Thrift 

Supervision,’’ and adding ‘‘and the 

Office of the Comptroller of the 

Currency,’’ in its place, and by removing 

‘‘parts 25, 228, or 563e’’ and adding 

‘‘parts 25, 195, or 228’’ in its place. 

§ 345.43 [Amended] 

■ 16. Section 345.43 is amended in 

paragraph (b)(2) by removing ‘‘part 203’’ 

and adding ‘‘part 1003’’ in its place. 

Dated: December 16, 2015. 

Amy S. Friend, 

Senior Deputy Comptroller and Chief 

Counsel. 

By order of the Board of Governors of the 

Federal Reserve System, acting through the 

Secretary of the Board under delegated 

authority, December 16, 2015. 

Robert deV. Frierson, 

Secretary of the Board. 

By order of the Board of Directors. 

Dated at Washington, DC, this 15th day of 

December, 2015. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2015–32670 Filed 12–28–15; 8:45 am] 

BILLING CODE 4810–33–P; 6210–01–6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1199; Directorate 

Identifier 2014–NM–008–AD; Amendment 

39–18351; AD 2015–26–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–07– 

10 for certain Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) 

airplanes. AD 2011–07–10 required 

revising the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness; doing detailed visual 

inspections; removing discrepant 

material; cleaning the surfaces of the 

valves, the plug of the sensing port, and 

the cabin pressure-sensing port plug; 

securing the insulation; installing a new 

safety valve, and replacing certain cabin 

pressure-sensing port plugs. This new 

AD retains all requirements of AD 2011– 

07–10, and requires a detailed visual 

inspection of both safety valves and the 

surrounding area for foreign material, 

room temperature vulcanizing (RTV) 

silicone, contamination, foam on the 

bulkhead structure, tape or insulation, 

and loose material; and corrective 

actions if necessary. This AD was 

prompted by reports of in-flight loss of 

cabin pressurization that was attributed 

to partial blockage of a safety valve 

cabin pressure-sensing port in 

conjunction with a failed safety valve 

manometric capsule. We are issuing this 

AD to detect and correct blockage of a 

safety valve cabin pressure-sensing port, 

which could result in loss of cabin 

pressure. 

DATES: This AD becomes effective 

February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 5, 2011 (76 FR 17758, 

March 31, 2011). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1199; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this final rule, contact Bombardier, Inc., 

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– 

1199. 

FOR FURTHER INFORMATION CONTACT: 

Luke Walker, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7363; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, 

March 31, 2011). AD 2011–07–10 

applied to certain Bombardier, Inc. 

Model BD–100–1A10 (Challenger 300) 

airplanes. The NPRM published in the 

Federal Register on April 15, 2015 (80 

FR 20181) (‘‘the NPRM’’). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–06R1, 

dated August 8, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model BD– 

100–1A10 (Challenger 300) airplanes. 

The MCAI states: 

Investigation of a high altitude loss of 

cabin pressurization on a BD–100–1A10 

aeroplane determined that it was caused by 

a partial blockage of a safety valve cabin 

pressure-sensing port, in conjunction with a 

dormant failure/leakage of the safety valve 

manometric capsule. The blockage, caused by 

accumulation of lint/dust on the grid of the 

port plug, did not allow sufficient airflow 

through the cabin pressure-sensing port to 

compensate for the rate of leakage from the 

manometric capsule, resulting in the opening 

of the safety valve. It was also determined 

that failure of the manometric capsule alone 

would not result in the opening of the safety 

valve. 

The original issue of this [Canadian] AD 

mandated a revision of the maintenance 

schedule, the cleaning of the safety valves, 

the removal of material from the area 

surrounding the safety valves and the 

modification of the safety valves with a 

gridless cabin pressure-sensing port plug. 

Since the original issue of this [Canadian] 

AD, there have been two additional reported 

events of in-flight loss of cabin pressurization 

that were attributed to partial blockage of a 

safety valve cabin pressure-sensing port in 

conjunction with a failed safety valve 

manometric capsule. 

Bombardier Aerospace has determined that 

aeroplanes with a particular interior 

installation require improved instructions to 


jstallworth on DSK7TPTVN1PROD with RULES
81166 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 

clean the safety valves and their surrounding 

area. In addition, Aircraft Maintenance 

Manual tasks have been updated to ensure 

that inspection of the safety valves and their 

surrounding is carried out after any 

maintenance action. 

Revision 1 of this [Canadian] AD is issued 

to mandate inspection and cleaning of the 

safety valves and their surrounding area on 

the affected aeroplanes. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1199- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Revised Docket Number 

We have changed the docket number 

specified in the NPRM from ‘‘Docket 

No. FAA–2015–0827’’ to ‘‘Docket No. 

FAA–2015–1199’’ in this final rule. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Service 

Bulletin 100–25–21, Revision 02, dated 

July 25, 2013. The service information 

describes procedures for a detailed 

visual inspection of both safety valves 

and the surrounding area for foreign 

material, RTV silicone, contamination, 

foam on the bulkhead structure, tape or 

insulation, and loose material, and 

applicable corrective actions. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 67 

airplanes of U.S. registry. 

The actions required by AD 2011–07– 

10, Amendment 39–16647 (76 FR 

17758, March 31, 2011), and retained in 

this AD take about 10 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

that were required by AD 2011–07–10 is 

$850 per product. 

We also estimate that it will take 

about 4 work-hours per product to 

comply with the new 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 $22,780, 

or $340 per product. 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1199; 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 

removing Airworthiness Directive (AD) 

2011–07–10, Amendment 39–16647 (76 

FR 17758, March 31, 2011), and adding 

the following new AD: 

2015–26–03 Bombardier, Inc.: Amendment 

39–18351. Docket No. FAA–2015–1199; 

Directorate Identifier 2014–NM–008–AD. 

(a) Effective Date 

This AD becomes effective February 2, 

2016. 

(b) Affected ADs 

This AD replaces AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) airplanes, 

certificated in any category, serial numbers 

20001 through 20274. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of inflight loss of cabin pressurization that were 

attributed to partial blockage of a safety valve 

cabin pressure-sensing port in conjunction 

with a failed safety valve manometric 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 81167 

capsule. We are issuing this AD to detect and 

correct blockage of a safety valve cabin 

pressure-sensing port, which could result in 

loss of cabin pressure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision with No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011), with no changes. For all airplanes: 

Within 30 days after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), revise the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness by incorporating Tasks 21–31– 

09–101 and 21–31–09–102 in the Bombardier 

Temporary Revision (TR) 5–2–53, dated 

October 1, 2009, to Section 5–10–40, 

‘‘Certification Maintenance Requirements,’’ 

in Part 2 of Chapter 5 of Bombardier 

Challenger 300 BD–100 Time Limits/

Maintenance Checks. 

(1) For the new tasks identified in 

Bombardier TR 5–2–53, dated October 1, 

2009: For airplanes identified in the ‘‘Phasein’’ section of Bombardier TR 5–2–53, dated 

October 1, 2009, the initial compliance with 

the new tasks must be carried out in 

accordance with the phase-in schedule 

detailed in Bombardier TR 5–2–53, dated 

October 1, 2009, except where that TR 

specifies a compliance time from the date of 

the TR, this AD requires compliance within 

the specified time after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)). 

Thereafter, except as provided by 

paragraph (n)(1) of this AD, no alternative to 

the task intervals may be used. 

(2) When the information in Bombardier 

TR 5–2–53, dated October 1, 2009, has been 

included in the general revisions of the 

applicable Airworthiness Limitations section, 

that TR may be removed from that 

Airworthiness Limitations section of the 

Instructions for Continued Airworthiness. 

(h) Retained Inspection, Removal, Cleaning, 

and Installation With Certain Clarified 

Compliance Times 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011), with certain clarified compliance 

times. For airplanes having S/Ns 20003 

through 20173 inclusive, 20176, and 20177: 

Within 50 flight hours after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), do a detailed visual inspection of the 

safety valves and surrounding areas for 

discrepant material (e.g., foreign material 

surrounding the safety valves, room 

temperature vulcanizing (RTV) sealant on 

safety valves, RTV excess on the bulkhead, 

tape near the safety valve opening, and, on 

certain airplanes, insulation near the safety 

valve opening, and foam in the area 

surrounding the safety valves) and a detailed 

visual inspection for contamination (e.g., 

RTV, dust, or lint) in the safety valve 

pressure ports, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–25–14, dated June 30, 

2008 (for airplanes having S/Ns 20124, 

20125, 20128, 20134, 20139, 20143, 20146, 

20148 through 20173 inclusive, 20176, and 

20177); or Bombardier Service Bulletin 100– 

25–21, dated June 30, 2008 (for airplanes 

having S/Ns 20003 through 20123 inclusive, 

20126, 20127, 20129 to 20133 inclusive, 

20135 to 20138 inclusive, 20140 through 

20142 inclusive, 20144, 20145, and 20147). 

(1) If any discrepant material is found 

during the detailed visual inspection, before 

further flight, remove the discrepant material, 

clean the surfaces of the valves, and secure 

the insulation, as applicable, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 100–25–14, 

dated June 30, 2008 (for airplanes having S/ 

Ns 20124, 20125, 20128, 20134, 20139, 

20143, 20146, 20148 through 20173 

inclusive, 20176, and 20177); or Bombardier 

Service Bulletin 100–25–21, dated June 30, 

2008 (for airplanes having S/Ns 20003 

through 20123 inclusive, 20126, 20127, 

20129 through 20133 inclusive, 20135 

through 20138 inclusive, 20140 through 

20142 inclusive, 20144, 20145, and 20147). 

(2) If contamination (e.g., RTV, dust, or 

lint) is found on the safety valve pressure 

sensing ports, before further flight, do a 

detailed visual inspection of the outside and 

inside diameters of the pressure sensing port 

conduit for the presence of RTV; and before 

further flight do the actions specified in 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD, 

as applicable; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–25–14, dated June 30, 

2008 (for airplanes having S/Ns 20124, 

20125, 20128, 20134, 20139, 20143, 20146, 

20148 through 20173 inclusive, 20176, and 

20177); or Bombardier Service Bulletin 100– 

25–21, dated June 30, 2008 (for airplanes 

having S/Ns 20003 through 20123 inclusive, 

20126, 20127, 20129 through 20133 

inclusive, 20135 through 20138 inclusive, 

20140 through 20142 inclusive, 20144, 

20145, and 20147). 

(i) If no RTV is found, clean the plug of the 

sensing port. 

(ii) If any RTV is found, install a new safety 

valve. 

(i) Retained Cleaning for Certain Airplanes 

With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–07–10, Amendment 

39–16647 (76 FR 17758, March 31, 2011), 

with no changes. For airplanes having S/Ns 

20174, 20175, 20178 through 20189 

inclusive, 20191 through 20228 inclusive, 

20230 through 20232 inclusive, 20235, 

20237, 20238, 20241, 20244, 20247, 20249 

through 20251 inclusive, 20254, 20256 and 

20259: Within 50 flight hours after June 1, 

2010 (the effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), clean the cabin pressure-sensing port 

plug in both safety valves, in accordance 

with Paragraph 2.B., ‘‘Part A—Modification— 

Cleaning,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

A100–21–08, dated June 18, 2009. 

(j) Retained Cleaning for Certain Other 

Airplanes With No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–07–10, Amendment 

39–16647 (76 FR 17758, March 31, 2011), 

with no changes. For airplanes having S/Ns 

20003 through 20189 inclusive, 20191 

through 20228 inclusive, 20230 through 

20232 inclusive, 20235, 20237, 20238, 20241, 

20244, 20247, 20249 through 20251 

inclusive, 20254, 20256, and 20259: Within 

50 flight hours after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), clean the cabin pressure-sensing port 

plug in both safety valves, in accordance 

with Paragraph 2.B., ‘‘Part A—Modification— 

Cleaning,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

A100–21–08, dated June 18, 2009. Repeat the 

cleaning thereafter at intervals not to exceed 

50 flight hours until the actions specified by 

paragraph (k) of this AD are completed. 

(k) Retained Replacement With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011), with no changes. For airplanes 

having S/Ns 20003 through 20189 inclusive, 

20191 through 20228 inclusive, 20230 

through 20232 inclusive, 20235, 20237, 

20238, 20241, 20244, 20247, 20249 through 

20251 inclusive, 20254, 20256, and 20259: 

Within 12 months after May 5, 2011 (the 

effective date of AD 2011–07–10), replace the 

cabin pressure-sensing port plug having part 

number (P/N) 2844–060 in both safety valves 

with a new gridless plug having P/N 2844– 

19 and re-identify the safety valves, in 

accordance with Paragraph 2.C., ‘‘Part B— 

Modification—Replacement,’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin A100–21–08, dated June 18, 

2009. Doing the actions in this paragraph 

terminates the repetitive cleanings required 

by paragraph (j) of this AD. 

(l) New Requirement of This AD: Inspection 

and Cleaning 

For airplanes having S/Ns 20003 through 

20123 inclusive, 20126, 20127, 20129 

through 20133 inclusive, 20135 through 

20138 inclusive, 20140 through 20142 

inclusive, 20144, 20145, and 20147: Within 

500 flight hours or 15 months after the 

effective date of this AD, whichever occurs 

first, do a detailed visual inspection of both 

safety valves and the surrounding area for 

foreign material, RTV silicone, 

contamination, foam on the bulkhead 

structure, tape or insulation, and loose 

material, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–25–21, Revision 02, 

dated July 25, 2013. Do all applicable 

corrective actions before further flight, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–25–21, Revision 02, dated July 25, 2013. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (l) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 


jstallworth on DSK7TPTVN1PROD with RULES
81168 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 

Bulletin 100–25–21, Revision 01, dated 

February 26, 2013, which is not incorporated 

by reference in this AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the New York 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: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

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

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2010–06R1, 

dated August 8, 2013, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2015–1199. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(5) and (p)(6) of this AD. 

(p) 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. 

(3) The following service information was 

approved for IBR on February 2, 2016. 

(i) Bombardier Service Bulletin 100–25–21, 

Revision 02, dated July 25, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 5, 2011, (76 FR 

17758, March 31, 2011). 

(i) Bombardier Service Bulletin A100–21– 

08, dated June 18, 2009. 

(ii) Bombardier Service Bulletin 100–25– 

14, dated June 30, 2008. 

(iii) Bombardier Service Bulletin 100–25– 

21, dated June 30, 2008. 

(iv) Bombardier Temporary Revision (TR) 

5–2–53, dated October 1, 2009, to Section 5– 

10–40, ‘‘Certification Maintenance 

Requirements,’’ in Part 2 of Chapter 5 of 

Bombardier Challenger 300 BD–100 Time 

Limits/Maintenance Checks. 

(5) 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. 

(6) 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. 

(7) 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 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32080 Filed 12–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0648; Directorate 

Identifier 2013–NM–136–AD; Amendment 

39–18344; AD 2015–25–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010–06– 

04, for certain Airbus Model A300 B2– 

1C, B2–203, B2K–3C, B4–103, B4–203, 

B4–2C airplanes; Model A310 series 

airplanes; Model A300 B4–600 series 

airplanes; and Model A300 B4–600R 

series airplanes. AD 2010–06–04 

required repetitive inspections to detect 

cracks of the pylon side panels (upper 

section) at rib 8; and corrective actions 

if necessary. This new AD continues to 

require repetitive inspections for 

cracking of the pylons 1 and 2 side 

panels (upper section) at rib 8 with 

reduced compliance times, and 

corrective actions if necessary. This AD 

also requires repetitive post-repair and 

post-modification inspections and 

repair if necessary. This AD also 

removes certain airplanes having a 

certain modification from the 

applicability. This AD was prompted by 

reports of cracks found on pylon side 

panels at rib 8 and a fleet survey and 

updated fatigue and damage tolerance 

analyses. We are issuing this AD to 

detect and correct cracking of pylon side 

panels (upper section) at rib 8, which 

could lead to reduced structural 

integrity of the pylon primary structure, 

which could cause detachment of the 

engine from the fuselage. 

DATES: This AD becomes effective 

February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 15, 2010 ((75 FR 

11428, March 11, 2010); corrected May 

4, 2010 (75 FR 23572)). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0648; 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– 

0648. 

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 to supersede AD 2010–06–04, 


jstallworth on DSK7TPTVN1PROD with RULES