3310 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

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): 

2016–01–15 Agusta S.p.A.: Amendment 39– 

18374; Docket No. FAA–2015–1935; 

Directorate Identifier 2014–SW–008–AD. 

(a) Applicability 

This AD applies to Agusta S.p.A. Model 

AB139 and AW139 helicopters, serial 

number (S/N) 31005 through 31517 (except 

S/N 31007, 31415, 31431, 31491, 31500, 

31508, and 31516) and S/N 41001 through 

41356 (except S/N 41355), certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a subfloor frame. This condition 

could result in failure of the pilot and copilot pedal support frame and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 25, 

2016. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 30 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 300 

hours TIS, using a light, inspect all visible 

surfaces of the left hand subfloor frame, right 

hand subfloor frame, and middle subfloor 

frame at station (STA) 2105 for a crack as 

shown in Figures 10 through 13 of 

AgustaWestland Bollettino Tecnico No. 139– 

311, Revision B, dated June 4, 2014 (BT 139– 

311). 

(2) If there is a crack, before further flight, 

install frame STA 2105 retromod part 

number (P/N) 3G5306P47211 by following 

the Compliance Instructions, Part II, 

paragraphs 7 through 7.10. of BT 139–311. 

(3) If there are no cracks, within 1200 

hours TIS, install frame STA 2105 retromod 

P/N 3G5306P47211 by following the 

Compliance Instructions, Part II, paragraphs 

7 through 7.10. of BT 139–311. 

(4) Installing frame STA 2105 retromod P/ 

N 3G5306P47211 terminates the repetitive 

inspection requirements in paragraph (e)(1) 

of this AD. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0048, dated March 4, 2014. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2015–1935. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5300, Fuselage Structure (General). 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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 the AD specifies otherwise. 

(i) AgustaWestland Bollettino Tecnico No. 

139–311, Revision B, dated June 4, 2014. 

(ii) Reserved. 

(3) For Agusta S.p.A. service information 

identified in this AD, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: Maurizio 

D’Angelo; telephone 39–0331–664757; fax 

39–0331–664680; or at http://

www.agustawestland.com/technicalbulletins. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on January 6, 

2016. 

Bruce E. Cain, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–00659 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–2014–0577; Directorate 

Identifier 2013–SW–042–AD; Amendment 

39–18375; AD 2015–12–09 R1] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising airworthiness 

directive (AD) 2015–12–09 for Airbus 

Helicopters Model EC135P1, EC135T1, 

EC135P2, EC135T2, EC135P2+, 

EC135T2+, and MBB–BK 117 C–2 

helicopters. AD 2015–12–09 required 

inspecting certain washers for 

movement and making the appropriate 

repairs if the washers move. As 

published, AD 2015–12–09 referenced 

an incorrect date for the service 

information in the Credit for Previous 

Actions section. This AD corrects the 

error while retaining the requirements 

of AD 2015–12–09. These actions are 

intended to prevent loss of concerned 

control axis and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective February 25, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of July 23, 2015 (80 FR 34831, June 

18, 2015). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

Room 6N–321, 10101 Hillwood Pkwy, 

Fort Worth, TX 76177. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0577; 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 European Aviation 

Safety Agency (EASA) AD, any 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3311 

incorporated-by-reference information, 

the economic evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy, Fort Worth, TX 76177; telephone 

(817) 222–5110; email matt.wilbanks@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 24, 2015, we issued a notice 

of proposed rulemaking (NPRM) to 

amend 14 CFR part 39 to revise AD 

2015–12–09, Amendment 39–18184 (80 

FR 34831, June 18, 2015), which applied 

to Airbus Helicopters Model EC135P1, 

EC135T1, EC135P2, EC135T2, 

EC135P2+, EC135T2+, and MBB–BK 

117 C–2 helicopters. The NPRM 

published in the Federal Register on 

August 3, 2015 (80 FR 45900). The 

NPRM was prompted by the discovery 

of an incorrectly dated Alert Service 

Bulletin (ASB) in the Credit for Previous 

Actions section of AD 2015–12–09. The 

NPRM proposed to retain the actions 

required by AD 2015–12–09 and correct 

the ASB date and revise other 

information throughout the AD. 

AD 2015–12–09 was prompted by AD 

No. 2013–0176, dated August 7, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Eurocopter Deutschland 

GmbH Model EC 135 P1 (CDS), EC 135 

P1 (CPDS), EC 135 P2+, EC 135 P2 

(CPDS), EC 135 T1 (CDS), EC 135 T1 

(CPDS), EC 135 T2+, EC 135 T2 (CPDS), 

EC 635 P2+, EC 635 T1 (CPDS), EC 635 

T2+, and MBB–BK 117 C–2 helicopters. 

EASA advises that during installation 

work on a helicopter, it was discovered 

that it was not possible to install 

attachment hardware on a threaded 

blind borehole between the Smart 

Electro Mechanical Actuator (SEMA) 

and the control rod without play. EASA 

advises that this condition, if not 

detected and corrected, could lead to 

loss of the concerned control axis, 

possibly resulting in loss of helicopter 

control. For these reasons, EASA AD 

No. 2013–0176 requires a one-time 

inspection of the affected SEMA 

attachment hardware to detect improper 

connection and play and, depending on 

the findings, replacement of the affected 

hardware. After the issuance of EASA 

AD No. 2013–0176, Eurocopter 

Deutschland GmbH changed its name to 

Airbus Helicopters Deutschland GmbH. 

When AD 2015–12–09 was published, 

an incorrect reference to the date of 

Eurocopter ASB EC135–22A–015, 

Revision 0, dated May 13, 2008, 

appeared in the text of the rule. 

Specifically, AD 2015–12–09 includes 

the following under paragraph (f), Credit 

for Previous Actions: ‘‘If you performed 

the actions in Eurocopter Alert Service 

Bulletin EC135–22A–015, Revision 0, 

dated May 13, 2018, or Eurocopter Alert 

Service Bulletin MBB BK117 C–2–22A– 

009, Revision 0, May 13, 2008, before 

the effective date of this AD, you met 

the requirements of this AD.’’ As 

published, the reference to May 13, 

2018, is incorrect. The correct date for 

Eurocopter ASB EC135–22A–015, 

Revision 0, is May 13, 2008. 

Accordingly, we are revising AD 

2015–12–09 to correct the date for 

Eurocopter ASB EC135–22A–015, 

Revision 0. Further, we updated the 

physical address of the FAA Southwest 

Regional Office throughout this AD and 

the email address for requesting an 

Alternative Method of Compliance 

(AMOC). We did not change any other 

part of the preamble or regulatory 

information. The final rule is reprinted 

in its entirety for the convenience of 

affected operators. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(80 FR 45900, August 3, 2015). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter reported in ASBs EC135– 

22A–015, Revision 1, dated January 28, 

2013, and MBB BK117 C–2–22A–009, 

Revision 1, dated August 3, 2009, that 

it was discovered during the installation 

work on a helicopter that it was not 

possible to establish attachment 

hardware on a threaded blind borehole 

between the SEMA and the control rod 

without play. The ASBs state that 

‘‘unfavourable adding of the tolerances’’ 

of the individual attachment hardware 

elements caused the screw to push 

against the bottom of the threaded blind 

borehole on the SEMA, preventing any 

clamping force on the screw head. The 

ASBs call for inspecting the SEMA 

attachment hardware connected to their 

respective control rods for play and 

making the proper adjustments to 

eliminate any play. 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 385 

helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 

Based on these estimates, we expect the 

following costs: 

• Inspecting for movement of the 

washers requires 1.5 work-hours for a 

labor cost of $128 per helicopter and 

$49,280 for the U.S. fleet. 

• Replacing the screws and related 

work requires an additional 0.5 workhours for a labor cost of $43. Screws 

cost $4 each while washers cost $10 

each. We estimate the cost at $79 per 

repair. 

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 have 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 


jstallworth on DSK7TPTVN1PROD with RULES
3312 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

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 

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. 

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) 

2015–12–09, Amendment 39–18184 (80 

FR 34831, June 18, 2015), and adding 

the following new AD: 

2015–12–09 R1 Airbus Helicopters 

Deutschland GmbH (Previously 

Eurocopter Deutschland GmbH) (Airbus 

Helicopters): Amendment 39–18375; 

Docket No. FAA–2014–0577; Directorate 

Identifier 2013–SW–042–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model EC135P1, EC135T1, EC135P2, 

EC135T2, EC135P2+, EC135T2+, and MBB– 

BK 117 C–2 helicopters, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loose attachment hardware between the 

Smart Electro Mechanical Actuator (SEMA) 

and a control rod. This condition could result 

in loss of the control axis and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 25, 

2016. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 50 hours time-in-service (TIS), 

for Model EC135P1, EC135T1, EC135P2, 

EC135T2, EC135P2+, and EC135T2+ 

helicopters, do the following: 

(i) Using Figure 1 and Figure 2 of 

Eurocopter Alert Service Bulletin EC135– 

22A–015, Revision 1, dated January 28, 2013 

(ASB EC135–22A–015) as reference, inspect 

the attachment hardware between the SEMA 

and the longitudinal actuator control rod to 

determine whether any of the washers can be 

moved. 

(A) If no washer can be moved, no further 

action is needed. 

(B) If a washer can be moved, replace the 

four screws and install two additional 

washers, part number (P/N) EN2139–05016, 

to connect the SEMA with the control rod. 

Torque-tighten each screw to 5–6 Nm. 

(ii) Using Figure 1 and Figure 2 of ASB 

EC135–22A–015 as reference, inspect the 

attachment hardware between the SEMA and 

the lateral actuator control rod to determine 

whether any of the washers can be moved. 

(A) If no washer can be moved, no further 

action is needed. 

(B) If a washer can be moved, replace the 

four screws and install two additional 

washers, P/N EN2139–05016, to connect the 

SEMA with the control rod. Torque-tighten 

each screw to 5–6 Nm. 

(iii) Using Figure 1, Figure 3, and Figure 

4 of ASB EC135–22A–015 as reference, 

inspect the attachment hardware between the 

SEMA and the yaw actuator control rod to 

determine whether any of the washers can be 

moved. 

(A) If no washer can be moved, no further 

action is needed. 

(B) If a washer can be moved, replace the 

four screws and install two additional 

washers, P/N EN2139–05016, to connect the 

SEMA with the control rod. Torque-tighten 

each screw to 5–6 Nm. 

(2) Within 50 hours TIS, for Model MBB 

BK117 C–2 helicopters, using Figure 1 of 

Eurocopter Alert Service Bulletin MBB 

BK117 C–2–22A–009, Revision 1, dated 

August 3, 2009, as reference, inspect the 

attachment hardware between the YawSEMA and the Yaw-SEMA control rod to 

determine whether any of the washers can be 

moved. 

(i) If no washer can be moved, no further 

action is needed. 

(ii) If a washer can be moved, replace the 

four screws and install two additional 

washers, P/N EN2139–05016, to connect the 

SEMA with the control rod. Torque-tighten 

each screw to 5–6 Nm and apply 

polyurethane lacquer onto the attachment 

hardware. 

(f) Affected ADs 

This AD revises AD 2015–12–09, 

Amendment 39–18184 (80 FR 34831, June 

18, 2015). 

(g) Credit for Previous Actions 

If you performed the actions in Eurocopter 

Alert Service Bulletin EC135–22A–015, 

Revision 0, dated May 13, 2008, or 

Eurocopter Alert Service Bulletin MBB 

BK117 C–2–22A–009, Revision 0, May 13, 

2008, before the effective date of this AD, you 

met the requirements of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

10101 Hillwood Pkwy, Fort Worth, TX 

76177; telephone (817) 222–5110; email 9- 

SW-FTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) AD 

No. 2013–0176, dated August 7, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA 2014–0577. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2213, Flight Controller. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 23, 2015, (80 FR 

34831, June 18, 2015). 

(i) Eurocopter Alert Service Bulletin 

EC135–22A–015, Revision 1, dated January 

28, 2013. 

(ii) Eurocopter Alert Service Bulletin MBB 

BK117 C–2–22A–009, Revision 1, dated 

August 3, 2009. 

(4) For Airbus Helicopters service 

information identified in this final rule, 

contact Airbus Helicopters, Inc., 2701 N. 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

(5) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, Room 6N–321, 10101 

Hillwood Pkwy, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(6) 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. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3313 

Issued in Fort Worth, Texas, on January 6, 

2016. 

Bruce E. Cain, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–00664 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–2014–0447; Directorate 

Identifier 2014–NM–019–AD; Amendment 

39–18368; AD 2016–01–09] 

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 Model DHC–8–400 series 

airplanes. This AD was prompted by a 

report of several cracks found on the 

forward passenger airstair door step 

assembly. This AD requires an 

inspection to determine the serial 

number of the airstair door step 

assembly, and if necessary, an electronic 

tap test, reidentification of the airstair 

door step assembly, and replacement of 

the airstair door step assembly. We are 

issuing this AD to detect and correct 

cracks in the forward passenger airstair 

door step assembly; such cracking could 

propagate and result in the structural 

failure of the steps and impede the 

evacuation of passengers in the event of 

an emergency egress situation. 

DATES: This AD becomes effective 

February 25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication 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-2014-0447; 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., 

Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0447. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Zimmer, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7306; 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 Model 

DHC–8–400 series airplanes. The NPRM 

published in the Federal Register on 

July 17, 2014 (79 FR 41661). The NPRM 

was prompted by a report of several 

cracks found on the forward passenger 

airstair door step assembly. The NPRM 

proposed to require an inspection to 

determine the serial number of the 

airstair door step assembly, and if 

necessary, an electronic tap test, 

reidentification of the airstair door step 

assembly, and replacement of the 

airstair door step assembly. We are 

issuing this AD to detect and correct 

cracks in the forward passenger airstair 

door step assembly; such cracking could 

propagate and result in the structural 

failure of the steps and impede the 

evacuation of passengers in the event of 

an emergency egress situation. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–20R1, 

dated December 30, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

There has been one in-service report of 

several cracks being found on the forward 

passenger airstair door step assembly 

between the steps and the sidewall panels. 

The investigation revealed that the 

application of potting compound may have 

been omitted during the bonding at the joint 

of the airstair door steps and the sidewalls. 

The omission of potting compound could 

cause the bonding sealant to crack. The 

cracks, if not detected, could propagate to 

result in the structural failure of the steps. 

In the event of an emergency egress 

situation, the failure of the airstair step 

assembly could impede the evacuation of 

passengers. 

This [Canadian] AD mandates the 

replacement of the affected forward 

passenger airstair step assembly with a new 

or reworked step assembly. 

Revision 1 of this [Canadian] AD provides 

additional instructions for performing an 

electronic tap test of the airstair step 

assembly if the Serial Number (S/N) of the 

airstair step assembly cannot be found. 

Required actions include an 

inspection to determine the serial 

number of the airstair door step 

assembly, and if necessary, an electronic 

tap test and reidentification and 

replacement of the assembly. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0447- 

0004. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 41661, 

July 17, 2014) and the FAA’s response 

to each comment. 

Request To Refer to Latest Service 

Information 

Republic Airlines and Horizon Air 

requested that we revise the NPRM (79 

FR 41661, July 17, 2014) to refer to the 

latest service information. 

We agree with the request. The 

revised service information, Bombardier 

Service Bulletin 84–52–77, Revision C, 

dated June 5, 2014, provides minor 

wording changes but does not change 

the procedures or add any airplanes. We 

have revised paragraphs (g) and (h) in 

this AD to refer to the new service 

information, and added Bombardier 

Service Bulletin 84–52–77, Revision B, 

dated October 31, 2013, to paragraph (i) 

of this AD, to provide credit for 

previous actions done before the 

effective date of this AD. 

Request To Allow Records Review 

Horizon Air requested that we revise 

paragraph (g) of the proposed AD (79 FR 

41661, July 17, 2014) to allow a review 

of aircraft records, in addition to a 

physical inspection, as a way to 

determine the serial number of the 

airstair door step assembly. 

We disagree with the request. A 

review of aircraft records may provide 

an appropriate means to determine 

serial numbers. For the airstair door step 

assembly, however, we understand that 

operators may remove and exchange the 


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