Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32445 

(1) Before the accumulation of 13,875 total 

flight cycles. 

(2) Within 365 days or 1,000 flight cycles 

after the effective date of this AD, whichever 

occurs first. 

(p) New Service Information Exception 

If any cracking is found during any 

inspection required by this AD, and 

Lockheed Service Bulletin 093–53–105, 

Revision 3, dated May 31, 2013, specifies 

contacting Lockheed for appropriate action: 

Before further flight, repair the cracking in 

accordance with a method approved by the 

Manager, Atlanta ACO, FAA. As of the 

effective date of this AD, for a repair method 

to be approved by the Manager, Atlanta ACO, 

as required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

(q) New Pre-Structural Modification 

Inspections and Structural Modification 

Before the accumulation of 20,800 total 

flight cycles: Do the applicable actions 

specified in paragraphs (q)(1) and (q)(2) of 

this AD. 

(1) Perform pre-structural modification 

inspections by doing the actions required by 

paragraphs (j), (n), and (o) of this AD. 

(2) Perform a structural modification of the 

aft pressure bulkhead by removing and 

replacing all stringer end fittings with new or 

refurbished fittings at stringers 1 through 14, 

and 52 through 64, in accordance with the 

Accomplishment Instructions of Lockheed 

Service Bulletin 093–53–105, Revision 3, 

dated May 31, 2013. 

(r) New Post-Structural Modification 

Repetitive Inspections 

Within 13,875 flight cycles after 

performing the actions required by paragraph 

(q)(2) of this AD: Do the actions specified in 

paragraphs (j), (n), and (o) of this AD, and 

repeat thereafter at intervals not to exceed 

1,750 flight cycles. 

(s) No Reporting Requirement 

Although Lockheed Service Bulletin 093– 

53–105, Revision 3, dated May 31, 2013, 

referenced in this AD specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

(t) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta ACO, 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (u) of this AD. 

(2) 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. 

(u) Related Information 

For more information about this AD, 

contact Carl Gray, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 30337; 

phone: 404–474–5554; fax: 404–474–5605; 

email: carl.w.gray@faa.gov. 

(v) 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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 14, 2015. 

(i) Lockheed Service Bulletin 093–53–105, 

Revision 3, dated May 31, 2013 (The date of 

May 15, 2013, on page 1 of Lockheed Service 

Bulletin 093–53–105, Revision 3, dated May 

31, 2013, is incorrect and should be May 31, 

2013). 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on January 11, 1996 (60 FR 

66870, December 27, 1995). 

(i) Lockheed L–1011 Service Bulletin 093– 

53–105, Revision 1, dated November 17, 

1995. 

(ii) Reserved. 

(5) For Lockheed service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, L1011 Technical 

Support Center, Dept. 6A4M, Zone 0579, 86 

South Cobb Drive, Marietta, GA 30063–0579; 

telephone 770–494–5444; fax 770–494–5445; 

email L1011.support@lmco.com; Internet 

http://www.lockheedmartin.com/ams/tools/

TechPubs.html. 

(6) You may view this service information 

at 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 May 18, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13325 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1937; Directorate 

Identifier 2014–SW–067–AD; Amendment 

39–18171; AD 2015–11–08] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. (Agusta) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2014–02– 

08 for Agusta Model A109C, A109S, 

A109K2, A109E, and AW109SP 

helicopters. AD 2014–02–08 required 

inspecting the lock wires securing the 

tail rotor (T/R) duplex bearing locking 

nut (locking nut) to determine whether 

any lock wires are missing or damaged. 

This AD retains some of the 

requirements of AD 2014–02–08 but 

removes the terminating action, expands 

the applicability, and adds a daily pilot 

check. This AD was prompted by 

reports of loosening T/R locking nuts. 

These actions are intended to prevent 

failure of the T/R and subsequent loss 

of control of the helicopter. 

DATES: This AD becomes effective June 

24, 2015. 

We must receive comments on this 

AD by August 10, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office 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, the 

economic evaluation, any comments 


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received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For 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. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: 

Martin Crane, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email martin.r.crane@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

On January 16, 2014, we issued AD 

2014–02–08, Amendment 39–17736 (79 

FR 5257, January 31, 2014) for Agusta 

Model A109C, A109S, and A109K2 

helicopters, and certain serial-numbered 

Model A109E and AW109SP 

helicopters. AD 2014–02–08 required 

repetitively inspecting the lock wires 

securing the T/R locking nut to 

determine whether any lock wires are 

missing or damaged, installing a second 

lock wire if only one was installed, and 

reassembling the housing and slider 

group of the T/R rotating controls as 

terminating action for the inspections. 

AD 2014–02–08 was prompted by 

reports of loosening T/R locking nuts. 

Those actions are intended to prevent 

failure of the T/R and subsequent loss 

of control of the helicopter. 

AD 2014–02–08 was prompted by AD 

No. 2012–0195–E, dated September 24, 

2012, and corrected September 25, 2012, 

issued by EASA, the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for certain Agusta Model A109E, 

A109LUH, A109S, AW109SP, A109C, 

and A109K2 helicopters. EASA advised 

of the T/R locking nut loosening on 

Model A109 helicopters and that one or 

both of the lock wires securing the 

locking nut were either damaged or 

absent from the T/R. EASA states that 

this condition could lead to failure of 

the T/R function and subsequent loss of 

control of the helicopter. AD No. 2012– 

0195–E requires repetitively inspecting 

the lock wires and removing and 

reassembling the housing and slider 

group of the T/R rotating controls, 

which is terminating action for the 

inspections. 

Actions Since AD 2014–02–08 Was 

Issued 

Since we issued AD 2014–02–08 (79 

FR 5257, January 31, 2014), a failure of 

a T/R duplex bearing ring nut 

installation occurred after the housing 

and slider group of the T/R rotating 

controls had been reassembled. 

Therefore, we are superseding AD 2014– 

02–08 to remove the reassembly as 

terminating action. Because of 

additional reports of the loosening of 

the bearing locking nut and the 

increased risk of failure of a lock wire, 

we are retaining the 25-hour TIS 

inspection. We are also requiring a daily 

pilot check to enhance detection of a 

failure of a T/R duplex bearing ring nut 

installation. AD 2014–02–18 did not 

apply to certain serial-numbered 

helicopters because the terminating 

action had already been performed on 

those models. Because we have 

determined that the terminating action 

does not correct the unsafe condition, 

we have expanded the applicability to 

include all serial-numbered helicopters 

for the Model A109C, A109S, A109K2, 

A109E, and AW109SP. EASA has not 

changed any of the requirements in its 

AD, and Agusta has not revised its 

service information. 

We have also corrected the design 

holder’s name from AgustaWestland 

S.p.A. to Agusta S.p.A., as specified by 

the current FAA type certificate. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are issuing this AD because we 

evaluated all known information 

provided by EASA and determined that 

an unsafe condition is likely to exist or 

develop on other helicopters of these 

same type designs. 

Related Service Information 

Agusta issued Bollettino Tecnico (BT) 

Nos. 109–134, 109EP–121, 109S–48, 

109K–54, and 109SP–051, all dated 

September 21, 2012, for Model A109C, 

A109E, A109S, A109K2, and AW109SP 

helicopters. These BTs specify 

inspecting for the presence and 

condition of the two locking wires. The 

BTs also specify if one lock wire is 

present and no damage is reported, 

installing a second lock wire. The BTs 

specify if one or both of the lock wires 

are damaged, removing and 

disassembling the housing and slider 

group of the T/R controls. 

AD Requirements 

This AD expands the applicability to 

include all serial-numbered helicopters. 

This AD retains the initial and repetitive 

inspections required by AD 2014–02–08 

(79 FR 5257, January 31, 2014) and 

retains the requirement to remove and 

reassemble the housing and slider group 

of the T/R rotating controls if one or 

both lock wires are damaged. This AD 

also requires a daily pilot check of each 

lock wire securing the T/R locking nut. 

An owner/operator (pilot) may perform 

the required visual check and must 

enter compliance with the applicable 

paragraph of the AD into the helicopter 

maintenance record in accordance with 

14 CFR 43.9(a)(1) through (4) and 14 

CFR 91.417(1)(2)(v). A pilot may 

perform this check because it involves 

only looking at the visible area of the 

lock wire securing the T/R locking nut 

to the housing. This check is an 

exception to our standard maintenance 

regulations. 

Differences Between This AD and the 

EASA AD 

This AD requires a daily pilot check 

of the lock wire, while the EASA does 

not. The EASA AD requires removing 

and reassembling the housing and slider 


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group of the T/R rotating controls as 

terminating action, regardless of 

whether the lock wire is damaged, and 

this AD does not. The EASA AD applies 

to certain serial-numbered helicopters, 

and this AD applies to all serialnumbered helicopters of each model. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking 

then. 

Costs of Compliance 

We estimate that this AD affects 122 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs to comply with this AD. The 

average labor rate is estimated to be $85 

per work-hour. Inspecting the lock wire 

takes about 0.25 work-hour, and the 

required parts cost is negligible, for a 

cost per helicopter of $22 and a total 

cost to U.S. operators of $2,684 per 

inspection cycle. Removing and 

reassembling the housing and slider 

group of the T/R rotating controls 

requires about 8 work-hours for a cost 

per helicopter of $680. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to adopting this rule 

because the previously described unsafe 

condition can adversely affect the 

controllability of the helicopter. Since 

cases of loosening of the T/R duplex 

bearing locking nut continue to occur, 

we are requiring a daily pilot check, 

which must be performed within 24 

hours. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 AD 2014–02–08, Amendment 

39–17736 (79 FR 5257, January 31, 

2014), and adding the following new 

airworthiness directive (AD): 

2015–11–08 Agusta S.p.A. Helicopters 

(Agusta): Docket No. FAA–2015–1937; 

Amendment 39–18171, Directorate 

Identifier 2014–SW–067–AD. 

(a) Applicability 

This AD applies to Agusta Model A109C, 

A109S, A109K2, A109E, and AW109SP 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

missing or broken lock wire securing the tail 

rotor (T/R) duplex bearing locking nut 

(locking nut). This condition could result in 

loosening of the locking nut, failure of the 

T/R, and subsequent loss of control of the 

helicopter. 

(c) Affected ADs 

This AD supersedes AD 2014–02–08, 

Amendment 39–17736 (79 FR 5257, January 

31, 2014). 

(d) Comments Due Date 

We must receive comments by August 10, 

2015. 

(e) 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. 

(f) Required Actions 

(1) Within 24 hours and thereafter before 

the first flight of each day or at intervals not 

exceeding 24 hours, whichever occurs later, 

check each lock wire securing the T/R 

locking nut to the housing. The location of 

the housing wire is depicted in Figure 1 to 

paragraph (f)(1) of this AD. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(2) The actions required by paragraph (f)(1) 

may be performed by the owner/operator 

(pilot) holding at least a private pilot 

certificate and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with 14 CFR 43.9(a)(1) 

through (4) and 14 CFR 91.417(1)(2)(v). The 

record must be maintained as required by 14 

CFR 91.417, 121.380, or 135.439. 

(3) Within 5 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 25 

hours TIS, inspect each lock wire securing 

the T/R locking nut to the housing. 

(4) If one or both lock wires are missing or 

damaged, before further flight, remove and 

reassemble the housing and slider group of 

the T/R rotating controls. 

(g) Special Flight Permit 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Martin Crane, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

martin.r.crane@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 

(1) Agusta Bollettino Tecnico (BT) Nos. 

109–134, 109EP–121, 109S–48, 109K–54, and 

109SP–051, all dated September 21, 2012, 

which are not incorporated by reference, 

contain additional information about the 

subject of this AD. For 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. You may review a copy of the 


tkelley on DSK3SPTVN1PROD with RULESER09JN15.000</GPH>
Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32449 

service information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2012–0195–E, dated September 24, 2012, 

and corrected September 25, 2012. You may 

view the EASA AD on the Internet at 

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

FAA–2015–1937. 

(k) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400 Tail Rotor System. 

Issued in Fort Worth, Texas, on May 26, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13845 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0754; Directorate 

Identifier 2014–NM–136–AD; Amendment 

39–18156; AD 2015–10–01] 

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 DHC–8–400 

series airplanes. This AD was prompted 

by reports of hydraulic fluid loss from 

the reservoir of the main landing gear 

(MLG) alternate extension system. This 

AD requires inspection for correct 

assembly of the MLG alternate extension 

system reservoir lid, and corrective 

action if necessary. We are issuing this 

AD to, in the event of a failure of the 

primary MLG extension system, prevent 

failure of the alternate MLG extension 

system to fully extend the MLG into a 

down-and-locked position, which could 

result in collapse of both left-hand and 

right-hand MLG sides during 

touchdown. 

DATES: This AD becomes effective July 

14, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 14, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0754; 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 Bombardier service information 

identified in this AD, 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. For Parker 

service information identified in this 

AD, contact Parker Aerospace, 14300 

Alton Parkway, Irvine, CA 92618; 

phone: 949–833–3000; Internet: http://

www.parker.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–2014–0754. 

FOR FURTHER INFORMATION CONTACT: 

Fabio Buttitta, 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 516–228–7303; 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 

DHC–8–400 series airplanes. The NPRM 

published in the Federal Register on 

October 23, 2014 (79 FR 63341). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–15, 

dated June 6, 2014 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–400 series airplanes. The MCAI 

states: 

Several cases have been reported of hydraulic 

fluid loss from the main landing gear (MLG) 

alternate extension system reservoir and in 

one case, the reservoir was found empty. The 

cause was determined to be an incorrectly 

assembled reservoir lid. In the event of a 

failed primary MLG extension system, an 

alternate MLG extension system with an 

empty reservoir may not be able to fully 

extend the MLG into the down and locked 

position, resulting in an unsafe landing 

configuration. 

This [Canadian] AD mandates the [general 

visual] inspection of the MLG alternate 

extension system reservoir lid for correct 

assembly and the required rectification [i.e., 

corrective action which consists of repairing 

the lid assembly]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0754- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 63341, October 23, 2014) 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 except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

63341, October 23, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 63341, 

October 23, 2014). 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Service 

Bulletin 84–29–34, dated May 9, 2013, 

with the attached Parker Service 

Bulletin 82910012–29–431, dated 

October 22, 2012. This service 

information describes procedures to 

inspect the lid assembly of the MLG 

alternate extension system reservoir for 

correct assembly and 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 of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 173 

airplanes of U.S. registry. 

We also estimate that it will take 

about 4 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 $58,820, or $340 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 


tkelley on DSK3SPTVN1PROD with RULES