Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47543 

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(r) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2010–0192 

(corrected), dated October 11, 2010; and 

EASA Airworthiness Directive 2010–0193 

(corrected), dated October 11, 2010; for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (s)(5), (s)(6), and (s)(7) of this AD. 

(s) 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 September 10, 2013. 

(i) Airbus Mandatory Service Bulletin 

A330–27–3102, Revision 08, dated December 

6, 2007. 

(ii) Airbus Mandatory Service Bulletin 

A340–27–4107, Revision 08, dated December 

6, 2007. 

(iii) Task 27.40.00/02, Lubrication of 

Trimmable Horizontal Stabilizer (THS) 

Actuator Ball Screw Nut, of Airbus A330 

Maintenance Review Board Report (MRBR), 

Revision 12, dated July 1, 2010. 

(iv) Task 27.40.00/02, Lubrication of THS 

Actuator Ball Screw Nut, of Airbus A340 

MRBR, Revision 12, dated July 1, 2010. 

(v) A330 Airworthiness Limitations 

Section (ALS) Part 4—Ageing Systems 

Maintenance, Revision 02, dated December 

16, 2009. Only the title page and Record of 

Revision of this document contain the 

revision level; no other page of the document 

contains this information. The title page of 

this document does not contain an issue date. 

(vi) Airbus A330 ALS Part 4—Ageing 

Systems Maintenance, Revision 03, dated 

September 9, 2011. Only the title page and 

Record of Revision of this document contain 

the revision level; no other page of the 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(vii) Airbus A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 15, 2009. Only the title page and 

Record of Revision of this document contains 

the revision level; no other page of this 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(viii) Airbus A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

October 12, 2011. Only the title page and 

Record of Revision of this document contain 

the revision level; no other page of the 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(ix) Airbus A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 03, dated 

November 15, 2012. Only the title page and 

Record of Revision of this document contain 

the revision level; no other page of the 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(4) The following service information was 

approved for IBR on May 4, 2005 (60 FR 

16104, March 30, 2005). 

(i) Airbus Service Bulletin A330–27–3007, 

Revision 01, dated September 18, 1996. 

(ii) Airbus Service Bulletin A330–27–3015, 

dated June 7, 1995. 

(iii) Airbus Service Bulletin A330–27– 

3047, Revision 01, dated November 26, 1997. 

(iv) Airbus Service Bulletin A330–27– 

3050, dated November 15, 1996. 

(v) Airbus Service Bulletin A330–27–3052, 

Revision 03, dated December 5, 2001. 

(vi) Airbus Service Bulletin A330–27– 

3085, Revision 02, dated September 5, 2002. 

(vii) Airbus Service Bulletin A330–27– 

3093, Revision 01, dated September 5, 2002. 

(viii) Airbus Service Bulletin A330–55– 

3020, Revision 01, dated October 21, 1998. 

(ix) Airbus Service Bulletin A340–27– 

4007, dated April 7, 1994. 

(x) Airbus Service Bulletin A340–27–4025, 

dated June 7, 1995. 

(xi) Airbus Service Bulletin A340–27– 

4054, Revision 01, dated November 26, 1997. 

(xii) Airbus Service Bulletin A340–27– 

4057, dated November 15, 1996. 

(xiii) Airbus Service Bulletin A340–27– 

4059, Revision 03, dated December 5, 2001. 

(xiv) Airbus Service Bulletin A340–27– 

4089, Revision 02, dated September 5, 2002. 

(xv) Airbus Service Bulletin A340–27– 

4099, Revision 01, dated September 5, 2002. 

(xvi) Airbus Service Bulletin A340–55– 

4021, Revision 01, October 21, 1998. 

(5) For Airbus service information 

identified in this AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet: http:// 

www.airbus.com. 

(6) For TRW Aeronautical Systems, SAMM 

Avionique, and Lucas Aerospace service 

information identified in this AD, contact 

Goodrich Corporation, Actuation Systems, 

Stafford Road, Fordhouses, Wolverhampton 

WV10 7EH, England; telephone +44 (0) 1902 

624938; fax +44 (0) 1902 788100; email 

techpubs.wolverhampton@goodrich.com; 

Internet http://www.goodrich.com/TechPubs. 

(7) You may review copies of the 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. 

(8) 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 June 21, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18774 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0209; Directorate 

Identifier 2012–NM–127–AD; Amendment 

39–17514; AD 2013–14–09] 

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) 2012–14– 

04 for certain Bombardier, Inc. Model 

DHC–8–100, –200, and –300 series 

airplanes. AD 2012–14–04 required 

replacing certain parking brake 

accumulators. This new AD retains this 

requirement. This new AD also requires 

installing restraint devices around the 

parking brake accumulator end caps. We 

are issuing this AD to prevent failure of 

a parking brake accumulator screw cap 

or end cap resulting in loss of the 

number 2 hydraulic system and damage 

to airplane structures, which could 

adversely affect the controllability of the 

airplane. 

DATES: This AD becomes effective 

September 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 27, 2012 (77 FR 

42956, July 23, 2012). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 


tkelley on DSK3SPTVN1PROD with RULES
47544 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–14–04, 

which applies to the specified products. 

The NPRM was published in the 

Federal Register on March 26, 2013 (78 

FR 18257), and proposed to correct an 

unsafe condition for the specified 

products. Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, issued Canadian 

Airworthiness Directive CF–2011–29R1, 

dated May 24, 2012 (the Mandatory 

Continuing Airworthiness Information, 

referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Seven cases of on-ground hydraulic 

accumulator screw cap or end cap failure 

have been experienced on CL–600–2B19 

* * * aeroplanes, resulting in loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. To date, the lowest number of 

flight cycles accumulated at the time of 

failure has been 6991. 

Although there have been no failures to 

date on any DHC–8 aeroplanes, similar 

accumulators to those installed on the CL– 

600–2B19, Part Numbers (P/N)08–60162–001 

and 08–60162–002 (Parking Brake 

Accumulator), are installed on the aeroplanes 

listed in the Applicability section of this 

[TCCA] directive. 

A detailed analysis of the systems and 

structure in the potential line of trajectory of 

a failed screw cap/end cap for the 

accumulator has been conducted. It has 

identified that the worst-case scenarios 

would be the loss of number 2 hydraulic 

system, and damage to aeroplane structures. 

This [original TCCA] directive [which 

corresponds to FAA AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012)] gives instructions to determine the 

part number and serial number of the 

existing parking brake accumulator, and 

where applicable, replace the accumulator. 

Revision 1 of this [TCCA] AD mandates the 

installation of restraint devices around [all] 

the parking brake accumulator end caps to 

hold them in place in the event of an end cap 

failure. 

Uncontained failure of the parking brake 

accumulator screw caps and/or end caps 

could result in loss of the number 2 

hydraulic system, and damage to 

airplane structures, and could adversely 

affect the controllability of the airplane. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 18257 March 26, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available 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 (78 FR 

18257 March 26, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 18257 

March 26, 2013). 

Costs of Compliance 

We estimate that this AD will affect 

about 129 products of U.S. registry. 

The actions that were required by AD 

2012–14–04, Amendment 39–17118 (77 

FR 42956, July 23, 2012), and retained 

in this AD take about 2 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the currently 

required actions is $170 per product. 

We estimate that it will take about 15 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$5,302 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$848,433, or $6,577 per product. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 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: 


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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47545 

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) 

2012–14–04, Amendment 39–17118 (77 

FR 42956, July 23, 2012), and adding the 

following new AD: 

2013–14–09 Bombardier, Inc.: Amendment 

39–17514. Docket No. FAA–2013–0209; 

Directorate Identifier 2012–NM–127–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 10, 2013. 

(b) Affected ADs 

This AD supersedes AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–101, –102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes, certificated 

in any category, serial numbers 003 and 

subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by reports of 

hydraulic accumulator screw cap or end cap 

failure. We are issuing this AD to prevent 

failure of a parking brake accumulator screw 

cap or end cap resulting in loss of the 

number 2 hydraulic system and damage to 

airplane structures, which could adversely 

affect the controllability of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Inspection and Replacement 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012), with no changes. Within 2,000 flight 

hours or 12 months after August 27, 2012 

(the effective date of AD 2012–14–04), 

whichever occurs first: Inspect to determine 

the part number (P/N) and serial number of 

the parking brake hydraulic accumulator, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–32–170, dated February 25, 2011. A review 

of airplane maintenance records is acceptable 

in lieu of this inspection if the part number 

and serial number of the parking brake 

hydraulic accumulator can be conclusively 

determined from that review. 

(1) For accumulators not having P/N 

0860162001 or 0860162002: No further 

action is required by this paragraph. 

(2) For accumulators having P/N 

0860162001 or 0860162002: Before further 

flight, do the applicable actions specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. 

(i) If the serial number is listed in the table 

in paragraph 3.B.(2) of Bombardier Service 

Bulletin 8–32–170, dated February 25, 2011: 

No further action is required by this 

paragraph. 

(ii) If the serial number is not listed in the 

table in paragraph 3.B.(2) of Bombardier 

Service Bulletin 8–32–170, dated February 

25, 2011: Within 2,000 flight hours or 12 

months after August 27, 2012 (the effective 

date of AD 2012–14–04, Amendment 39– 

17118 (77 FR 42956, July 23, 2012)), 

whichever occurs first, replace the 

accumulator with a new non-suspect 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–172, dated March 15, 

2011. 

(h) Retained Parts Installation Prohibition 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012), with no changes. As of August 27, 

2012 (the effective date of AD 2012–14–04), 

no person may install a parking brake 

accumulator, P/N 0860162001 or 0860162002 

with a serial number that is not listed in the 

table in paragraph 3.B.(2) of Bombardier 

Service Bulletin 8–32–170, dated February 

25, 2011, on any airplane. 

(i) New Requirement of This AD: Install 

Restraint Devices on All Airplanes 

Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first: Install restraint devices around 

the parking brake hydraulic accumulator end 

caps by incorporating Bombardier ModSum 

8Q101901, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–169, Revision A, dated 

December 16, 2011. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

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

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 8–32–169, dated November 25, 2011, 

which is not incorporated by reference in this 

AD. 

(k) 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2011–29R1, 

dated May 24, 2012, for related information. 

This MCAI may be found in the AD docket 

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

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the address specified in 

paragraph (m)(5) of this AD. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 10, 2013. 

(i) Bombardier Service Bulletin 8–32–169, 

Revision A, dated December 16, 2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 27, 2012 (77 FR 

42956, July 23, 2012). 

(i) Bombardier Service Bulletin 8–32–170, 

dated February 25, 2011. 

(ii) Bombardier Service Bulletin 8–32–172, 

dated March 15, 2011. 

(5) For 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. 

(6) You may review copies of the 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 July 5, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18771 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 


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