43938 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 

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): 

2015–15–09 BAE Systems (Operations) 

Limited: Amendment 39–18218. Docket 

No. FAA–2015–2957; Directorate 

Identifier 2015–NM–089–AD. 

(a) Effective Date 

This AD becomes effective August 10, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to BAE Systems 

(Operations) Limited Model 4101 airplanes, 

certificated in any category, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by a report that the 

pitch trim jammed in the fully down position 

due to incorrectly adjusted travel stops of the 

pitch trim servo motor, causing parts of the 

stop plates to break off and allowing the 

servo motor to force contact of the swaged 

stop on the trim cable with the stop plates. 

We are issuing this AD to detect and correct 

broken stop arms of the stop plates, which 

could lead to the pitch trim jamming, loss of 

control of the elevator trim, and possible 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) One-Time Inspection 

Within 30 days after the effective date of 

this AD: Do a one-time detailed inspection 

for damage of the stop arms of the stop 

plates, and an adjustment of the electric trim 

limit switches, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin J41–27–068, dated January 

21, 2014. If any damage is found, before 

further flight, replace the stop plate with a 

newly manufactured stop plate made of 

tufnol, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin J41–27–068, dated January 

21, 2014. 

(h) 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1175; 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 BAE Systems (Operations) 

Limited’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2015–0099, dated June 3, 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– 

2015–2957. 

(j) 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) BAE Systems (Operations) Limited 

Inspection Service Bulletin J41–27–068, 

dated January 21, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact BAE Systems (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone: +44 1292 675207; fax: +44 1292 

675704; email: RApublications@

baesystems.com; Internet http://

www.baesystems.com/Businesses/

RegionalAircraft/index.htm. 

(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 July 15, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–17933 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0088; Directorate 

Identifier 2014–NM–179–AD; Amendment 

39–18217; AD 2015–15–08] 

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 BD–100–1A10 

(Challenger 300) airplanes. This AD was 

prompted by testing of the spoiler 

electronic control unit (SECU) software 

for an upgrade, which revealed a timing 

error between the command and 

monitor channels. This AD requires 

revising the maintenance or inspection 

program to incorporate repetitive 

operational tests of the aileron 

disconnect system, and corrective action 

if necessary. This AD also requires 

modification and reidentification of the 

SECU, which would terminate the 

repetitive operational tests. We are 

issuing this AD to prevent a timing error 

in the SECU software, which, in 

combination with failure of the roll 

disconnect switch, could result in 

complete loss of spoiler functionality 

and consequent reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

August 28, 2015. 


rmajette on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 43939 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 28, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0088 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– 

0088. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Service Branch, ANE–172, 

FAA, New York Aircraft Certification 

Office, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7301; 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 

BD–100–1A10 (Challenger 300) 

airplanes. The NPRM published in the 

Federal Register on February 18, 2015 

(80 FR 8564). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–24, 

dated August 5, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on certain Bombardier, Inc. Model BD– 

100–1A10 (Challenger 300) airplanes. 

The MCAI states: 

During testing of the software for an 

upgrade of the spoiler electronic control unit 

(SECU), a timing error between the Command 

and Monitor channels was found in the 

SECU software. This timing error, if not 

corrected, in combination with the failure of 

the roll disconnect switch, may lead to a 

complete loss of spoiler functionality and 

result in a reduction or complete loss of 

aeroplane roll control. 

This [Canadian] AD mandates the SECU 

software modification to correct the timing 

error and to change the inspection interval 

for a maintenance task based on System 

Functional Hazard Analysis [by revising the 

inspection or maintenance program]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2015-0088-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 8564, February 18, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, with minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 8564, 

February 18, 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 8564, 

February 18, 2015). 

Related Service Information Under 1 

CFR Part 51 

Bombardier, Inc. has issued Service 

Bulletin 100–27–16, dated October 31, 

2013. The service information describes 

procedures for modification and 

reidentification of the SECU. 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 107 

airplanes of U.S. registry. 

We also estimate that it takes up to 6 

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 

up to $54,570, or up to $510 per 

product. 

We have received no definitive data 

on the parts cost for doing the 

modification 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-2015-0088; 

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, 


rmajette on DSK2VPTVN1PROD with RULES
43940 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 

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): 

AD 2015–15–08 Bombardier, Inc.: 

Amendment 39–18217. Docket No. 

FAA–2015–0088; Directorate Identifier 

2014–NM–179–AD. 

(a) Effective Date 

This AD becomes effective August 28, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

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

equipped with a spoiler electronic control 

unit (SECU) having part number (P/N) 

C47330–006, C47330–007, or C47330–008; 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by testing of the 

spoiler electronic control unit (SECU) 

software for an upgrade, which revealed a 

timing error between the command and 

monitor channels. We are issuing this AD to 

prevent a timing error in the SECU software, 

which, in combination with failure of the roll 

disconnect switch, could result in complete 

loss of spoiler functionality and consequent 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of the Maintenance or 

Inspection Program 

Within 600 flight hours since the most 

recent operational test of the aileron 

disconnect system for spoiler functionality as 

of the effective date of this AD, or within 400 

flight hours after the effective date of this AD, 

whichever occurs first: Revise the 

maintenance or inspection program, as 

applicable, to incorporate repetitive 

operational tests of the aileron disconnect 

system for spoiler functionality, and all 

applicable corrective actions, using a method 

approved by the Manager, New York ACO, 

ANE–170, FAA. 

Note 1 to paragraph (g) of this AD: 

Guidance on operational tests of the aileron 

disconnect system can be found in the 

Bombardier Inc., BD–100–1A10 Time Limits/ 

Maintenance Checks (TLMC) Manual. 

(h) Modification of the SECU 

Within 1,600 flight hours or 48 months 

after the effective date of this AD, whichever 

occurs first: Modify and re-identify the 

SECU, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–27–16, dated October 

31, 2013. Doing the actions required by this 

paragraph terminates the actions required by 

paragraph (g) of this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an SECU, P/N C47330– 

006, C47330–007, or C47330–008, on any 

airplane. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

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

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

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

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–24, dated 

August 5, 2014, 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 it in Docket No. 

FAA–2015–0088–0002. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 100–27–16, 

dated October 31, 2013. 

(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 July 15, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–17937 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1052; Directorate 

Identifier 2014–NM–140–AD; Amendment 

39–18210; AD 2015–15–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2004–13– 

02, which applied to certain The Boeing 

Company Model 747–100, –200B, and 

–200F series airplanes. AD 2004–13–02 

required repetitive inspections to find 

discrepancies in the upper and lower 

skins of the fuselage lap joints, and 

repair if necessary. This new AD adds 

post-repair inspections for cracking and 

corrosion, and repair if necessary; 

structural modification at the lap joints; 

and post-modification inspections for 

cracking and corrosion, and repair if 

necessary. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) that indicates the 

longitudinal lap joints are subject to 

widespread fatigue damage (WFD). The 

actions mandated by this AD are 

necessary to reach the limit of validity 

(LOV). We are issuing this AD to detect 

and correct fatigue cracking in the upper 

and lower skins of the fuselage lap 

joints, which could result in sudden 

fracture and failure of a lap joint and 

rapid in-flight decompression of the 

airplane fuselage. 


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