Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46317 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

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/

code_of_federal_regulations/ibr

_locations.html. 

TABLE 4—MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision level Date 

Airbus Mandatory Service Bulletin A330–27A3154, excluding Appendix 1 ................................... 01 July 25, 2008. 

Airbus Mandatory Service Bulletin A340–27A4154, excluding Appendix 1 ................................... 01 July 25, 2008. 

Airbus Service Bulletin A330–27–3110 .......................................................................................... 03 September 3, 2008. 

Airbus Service Bulletin A340–27–4115 .......................................................................................... 01 March 2, 2007. 

Issued in Renton, Washington, on August 

26, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21408 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0526; Directorate 

Identifier 2009–NM–029–AD; Amendment 

39–16008; AD 2009–18–12] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–400 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Four aircraft have experienced a dual AC 

[alternating current] generator shutdown, 

caused by a broken propeller de-ice bus bar 

which short-circuited with the backplate 

assembly. 

* * * A short circuit can cause a dual AC 

generator shutdown that, particularly in 

conjunction with an engine failure in icing 

conditions, could result in reduced 

controllability of the aircraft. 

* * * * * 

Reduced controllability of the 

airplane in certain operating conditions 

affects continued safe flight and 

landing. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

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: 

Wing Chan, Aerospace Engineer, 

Aerospace Engineer, Systems and Flight 

Test Branch, ANE–172, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7311; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 10, 2009 (74 FR 27476). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Four aircraft have experienced a dual AC 

[alternating current] generator shutdown, 

caused by a broken propeller de-ice bus bar 

which short-circuited with the backplate 

assembly. 

It was subsequently determined that any 

friction or contact between a propeller de-ice 

bus bar and the backplate assembly can cause 

an intermittent short circuit. Such a short 

circuit can cause a dual AC generator 

shutdown that, particularly in conjunction 

with an engine failure in icing conditions, 

could result in reduced controllability of the 

aircraft. 

This [Transport Canada Civil Aviation] 

directive mandates revision of the Airplane 

Flight Manual (AFM) to introduce a 

procedure that restores AC power following 

a failure of No. 1 and No. 2 AC generators 

with propeller de-ice on. Additionally, in 

order to prevent similar dual AC generator 

shutdowns, it mandates the application of 

sealant as insulation between the propeller 

de-ice bus bars and the backplate assembly. 

Reduced controllability of the 

airplane in certain operating conditions 

affects continued safe flight and 

landing. 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 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 the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

62 products of U.S. registry. We also 

estimate that it will take about 6 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 


jlentini on DSKJ8SOYB1PROD with RULES
46318 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 

cost of this AD to the U.S. operators to 

be $29,760, or $480 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 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); and 

3. 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 the NPRM, 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. Comments will be available in 

the AD docket shortly after receipt. 

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 AD: 

2009–18–12 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–16008. 

Docket No. FAA–2009–0526; Directorate 

Identifier 2009–NM–029–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 14, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–400, DHC–8–401, and DHC–8–402 

series airplanes, certificated in any category, 

serial numbers 4001, 4003, 4004, 4006, and 

4008 through 4154 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 61: Propellers/Propulsors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Four aircraft have experienced a dual AC 

[alternating current] generator shutdown, 

caused by a broken propeller de-ice bus bar 

which short-circuited with the backplate 

assembly. 

It was subsequently determined that any 

friction or contact between a propeller de-ice 

bus bar and the backplate assembly can cause 

an intermittent short circuit. Such a short 

circuit can cause a dual AC generator 

shutdown that, particularly in conjunction 

with an engine failure in icing conditions, 

could result in reduced controllability of the 

aircraft. 

This [Transport Canada Civil Aviation] 

directive mandates revision of the Airplane 

Flight Manual (AFM) to introduce a 

procedure that restores AC power following 

a failure of No. 1 and No. 2 AC generators 

with propeller de-ice on. Additionally, in 

order to prevent similar dual AC generator 

shutdowns, it mandates the application of 

sealant as insulation between the propeller 

de-ice bus bars and the backplate assembly. 

Reduced controllability of the airplane in 

certain operating conditions affects 

continued safe flight and landing. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 30 days after the effective date 

of this AD, revise the Limitations Section of 

the Bombardier Dash 8 Q400 AFM, PSM 1– 

84–1A, by inserting a copy of Bombardier 

Dash 8 Q400 Temporary Amendment (TA) 

14, Issue 1, dated May 10, 2006. When the 

information in Bombardier TA 14, Issue 1, 

dated May 10, 2006, is included in the 

general revisions of the AFM, the general 

revisions may be inserted in the AFM and the 

TA may be removed. 

(2) Within 5,000 flight hours after the 

effective date of this AD: Apply sealant 

between the bus bar assemblies and the 

backplate assembly by incorporating 

Bombardier DHC–8–400 Modification 

Summary 4–163047, Revision B, dated 

August 22, 2008, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–61–03, Revision ‘A,’ 

dated September 18, 2008. 

(3) Incorporating Bombardier DHC–8–400 

Modification Summary Package 4–163047 

before the effective date of this AD in 

accordance with Bombardier Service Bulletin 

84–61–03, dated April 27, 2007, is 

considered acceptable for compliance with 

the requirements of paragraph (f)(2) of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Wing 

Chan, Aerospace Engineer, Systems and 

Flight Test Branch, ANE–172, FAA, New 

York ACO, 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone (516) 

228–7311; fax (516) 794–5531. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(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 FAAapproved 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46319 

Related Information 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–01, dated January 19, 

2009; Bombardier Dash 8 Q400 TA 14, Issue 

1, dated May 10, 2006; and Bombardier 

Service Bulletin 84–61–03, Revision ‘A,’ 

dated September 18, 2008; for related 

information. 

Material Incorporated by Reference 

(i) You must use Bombardier Dash 8 Q400 

Temporary Amendment 14, Issue 1, dated 

May 10, 2006; and Bombardier Service 

Bulletin 84–61–03, Revision ‘A,’ dated 

September 18, 2008; as applicable; to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) 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; e-mail 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

18, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–20836 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0563; Directorate 

Identifier 2008–NM–180–AD; Amendment 

39–16005; AD 2009–18–09] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0070 and 0100 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A recent design review has been carried 

out on the F28 Mark 0070/0100 fuel system 

in accordance with the guidelines related to 

FAA SFAR 88 [Special Federal Aviation 

Regulation No. 88] (Fuel Tank Safety 

Program) and JAA [Joint Aviation 

Authorities] INT/POL/25/12. The review 

revealed that under certain failure 

conditions, prolonged dry running of the fuel 

transfer pumps may result in an ignition 

source in the centre wing fuel tank. This 

condition, if not corrected, could lead to 

ignition of flammable fuel vapors, resulting 

in fuel tank explosion and consequent loss of 

the aircraft. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2009. 

On October 27, 1999 (64 FR 51202, 

September 22, 1999), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 19, 2009 (74 FR 29144), 

and proposed to supersede AD 99–20– 

01, Amendment 39–11329 (64 FR 

51202, September 22, 1999). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

A recent design review has been carried 

out on the F28 Mark 0070/0100 fuel system 

in accordance with the guidelines related to 

FAA SFAR 88 [Special Federal Aviation 

Regulation No. 88] (Fuel Tank Safety 

Program) and JAA [Joint Aviation 

Authorities] INT/POL/25/12. The review 

revealed that under certain failure 

conditions, prolonged dry running of the fuel 

transfer pumps may result in an ignition 

source in the centre wing fuel tank. This 

condition, if not corrected, could lead to 

ignition of flammable fuel vapors, resulting 

in fuel tank explosion and consequent loss of 

the aircraft. 

To address and correct this unsafe 

condition, new software (version V13.55) has 

been developed for the Flight Warning 

Computer (FWC). This software update 

introduces a decreased time delay of the 

centre wing fuel tank low pressure alert from 

15 minutes to 60 seconds, to stop prolonged 

dry running of the fuel transfer pumps. 

For the reasons described above, this EASA 

Airworthiness Directive (AD) requires the 

replacement of the FWC with a modified 

unit, incorporating software version V13.55. 

The corrective actions include 

revising the airplane flight manual 

(AFM) to change certain indications and 

warnings; installing new software for 

the multifunction display unit (MFDU); 

and installing a new resistor in the 

thrust reverser indicator and control 

system, or an improved thrust reverser 

unlock indication relay. 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 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 the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a note within the AD. 


jlentini on DSKJ8SOYB1PROD with RULES