Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 3347 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Before using any AMOC approved 

in accordance with § 39.19 on any airplane 

to which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding 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 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. 

(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. 

Related Information 

(g) Refer to MCAI European Aviation 

Safety Agency (EASA) Emergency 

Airworthiness Directive 2006–0330-E, dated 

October 25, 2006; and Dassault Service 

Bulletins F900–366 and F900EX–277, both 

dated July 19, 2006; for related information. 

Material Incorporated by Reference 

(h) You must use Dassault Service Bulletin 

F900–366, dated July 19, 2006; or Dassault 

Service Bulletin F900EX–277, dated July 19, 

2006; 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 Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 98057–

3356; or 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 January 

12, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 07–258 Filed 1–24–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26050; Directorate 

Identifier 2006–NM–078–AD; Amendment 

39–14890; AD 2007–02–03] 

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: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Bombardier 

Model DHC–8–400 series airplanes. 

That AD currently requires revising the 

airplane flight manual (AFM) to advise 

the flightcrew of appropriate procedures 

to follow in the event that a main 

landing gear (MLG) fails to extend 

following a gear-down selection. That 

AD also currently requires repetitive 

replacement of the left and right MLG 

uplock assemblies with new assemblies; 

and an inspection of the left and right 

MLG uplock rollers for the presence of 

an inner low friction liner, and 

corrective actions if necessary. This new 

AD revises the requirement for replacing 

the left and right MLG uplock 

assemblies by allowing replacement 

with alternative parts. For a certain 

MLG uplock assembly, this new AD 

requires repetitive inspections of the 

uplock hatch lower jaw for the presence 

of a wear groove and replacement with 

an improved part if necessary. For a 

certain MLG uplock assembly, this new 

AD requires repetitive inspections of the 

uplock roller to ensure that it rotates 

freely and replacement with a new part 

if necessary. This new AD allows 

optional replacement of the left and 

right MLG uplock assemblies with 

improved parts, which ends the 

requirements of the AFM revision and 

repetitive replacement and inspections. 

This new AD removes airplanes from 

the applicability. This AD results from 

development of a terminating action. 

We are issuing this AD to ensure that 

the flightcrew has the procedures 

necessary to address failure of an MLG 

to extend following a gear-down 

selection; and to detect and correct such 

failure, which could result in a gear-up 

landing and possible injury to 

passengers and crew. 

DATES: This AD becomes effective 

March 1, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 1, 2007. 

On April 23, 2002 (67 FR 19101, April 

18, 2002), the Director of the Federal 

Register approved the incorporation by 

reference of Bombardier DHC–8 Alert 

Service Bulletin A84–32–15, dated 

February 4, 2002. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 

1Y5, Canada, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ezra 

Sasson, 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) 228–7320; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2002–08–05, amendment 

39–12713 (67 FR 19101, April 18, 2002). 

The existing AD applies to certain 

Bombardier Model DHC–8–400 series 

airplanes. That NPRM was published in 

the Federal Register on October 13, 

2006 (71 FR 60450). That NPRM 

proposed to continue to require revising 

the airplane flight manual (AFM) to 

advise the flightcrew of appropriate 

procedures to follow in the event that a 

main landing gear (MLG) fails to extend 

following a gear-down selection. That 

NPRM also proposed to continue to 

require repetitive replacement of the left 

and right MLG uplock assemblies with 

new assemblies; and an inspection of 

the left and right MLG uplock rollers for 

the presence of an inner low friction 

liner, and corrective actions if 

necessary. That NPRM also proposed to 

revise the requirement for replacing the 


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3348 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 

left and right MLG uplock assemblies by 

allowing replacement with alternative 

parts. For a certain MLG uplock 

assembly, that NPRM also proposed to 

require repetitive inspections of the 

uplock hatch lower jaw for the presence 

of a wear groove and replacement with 

an improved part if necessary. For a 

certain MLG uplock assembly, that 

NPRM also proposed to require 

repetitive inspections of the uplock 

roller to ensure that it rotates freely and 

replacement with a new part if 

necessary. That NPRM also proposed to 

allow optional replacement of the left 

and right MLG uplock assemblies with 

improved parts, which would end the 

requirements of the AFM revision and 

repetitive replacements and inspections. 

That NPRM also proposed to remove 

airplanes from the applicability. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the one comment that has 

been received on the NPRM. 

Request To Provide Additional 

Terminating Action 

Horizon Air requests that we revise 

paragraph (k) of the NPRM to provide an 

additional terminating action by 

allowing replacement with a new or 

overhauled uplock assembly having part 

number (P/N) 46500–9. Paragraph (k) of 

the NPRM proposed only to allow 

replacement of uplock assemblies 

having P/N 46500–3 or –5 with new or 

overhauled uplock assemblies having P/ 

N 46500–7. As justification, the 

commenter states that P/N 46500–9 is 

the latest version of the uplock 

assembly. The commenter also points 

out that Bombardier DHC–8 Service 

Bulletin 84–32–46, dated July 4, 2006, 

provides instructions for modifying an 

uplock assembly having P/N 46500–7 

and reidentifying it as P/N 46500–9. 

We agree to revise paragraph (k) of 

this AD to provide P/N 46500–9 as a 

terminating action. We have also revised 

paragraphs (g) and (i)(1) of this AD to 

allow replacement with P/N 46500–9. 

Bombardier DHC–8 Service Bulletin 84–

32–46 modifies an uplock assembly 

having P/N 46500–7 by improving 

retention of the proximity sensor target. 

Therefore, we have determined that a 

new or overhauled uplock assembly 

having P/N 46500–9 is also adequate for 

addressing the unsafe condition of this 

AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

The following table provides the 

estimated costs, at an average labor rate 

of $80 per work hour, for U.S. operators 

to comply with this AD. 

ESTIMATED COSTS

Action Work 

hours Parts Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

AFM revision (required by AD 2002–08–05) ........... 1 None $80 ................................. 21 $1,680. 

Replacement of uplock assemblies (required by AD 

2002–08–05).

4 1 $0 $320, per replacement 

cycle.

21 $6,720 per replacement 

cycle. 

Inspection of uplock rollers (required by AD 2002– 

08–05).

1 None $80 ................................. 21 $1,680. 

Inspections of uplock assemblies and uplock rollers 

(new action).

5 None $400 ............................... 21 $8,400. 

Terminating action (new action) ............................... 4 1 $0 $320 ............................... 21 $6,720. 

1The parts manufacturer states that it will supply required parts to operators at no cost. 

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 

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); 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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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: 


ycherry on PROD1PC64 with RULES
Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 3349 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–12713 (67 

FR 19101, April 18, 2002) and by adding 

the following new airworthiness 

directive (AD): 

2007–02–03 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–14890. 

Docket No. FAA–2006–26050; 

Directorate Identifier 2006–NM–078–AD. 

Effective Date 

(a) This AD becomes effective March 1, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2002–08–05. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–400 series airplanes, certificated in 

any category; serial numbers 4001 and 4003 

through 4087 inclusive; equipped with main 

landing gear (MLG) uplock assembly part 

numbers (P/Ns) 46500–3 and –5. 

Unsafe Condition 

(d) This AD results from development of a 

terminating action. We are issuing this AD to 

ensure that the flightcrew has the procedures 

necessary to address failure of an MLG to 

extend following a gear-down selection; and 

to detect and correct such failure, which 

could result in a gear-up landing and 

possible injury to passengers and crew. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2002–08–05 

Revision of FAA-Approved Airplane Flight 

Manual (AFM) 

(f) Within 3 days after April 23, 2002 (the 

effective date of AD 2002–08–05), amend all 

copies of the FAA-approved Bombardier 

Series 400 AFM, PSM 1–84–1A (for Models 

400, 401, and 402), by adding the following 

procedure to the Limitations section of the 

AFM and opposite page 4–21–1 of the AFM; 

and advise all flightcrew members of these 

changes. (The revision may be accomplished 

by inserting a copy of this AD into the 

Limitations section of the AFM and affected 

paragraphs of the AFM.): 

‘‘If ONE main landing gear fails to extend 

after performing landing gear extension per 

normal procedures given in paragraph 4.3.7 

and alternate extension procedures per 

paragraph 4.21.1 of the AFM: 

1. Visually confirm that the affected gear 

has not extended and that the associated 

doors have opened. 

2. Ensure No. 2 hydraulic system pressure 

and quantity are normal and the following 

landing gear advisory lights are illuminated: 

selector lever amber, gear green locked down 

(nose and non-affected main gear), red gear 

unlocked (affected main gear) and all amber 

doors open. 

3. NOSE L/G RELEASE handle—Return to 

the stowed position. 

4. LANDING GEAR ALTERNATE 

EXTENSION door—Close fully. 

5. MAIN L/G RELEASE handle—Return to 

the stowed position. 

6. LANDING GEAR ALTERNATE 

RELEASE door—Close fully. 

7. LANDING GEAR lever—DN. 

8. L/G DOWN SELECT INHIBIT SW—

Normal and guarded. Check amber doors 

open advisory lights out (nose and nonaffected main gear) and LDG GEAR INOP 

caution light out. 

9. LANDING GEAR lever—UP Check all 

gear, door and LANDING GEAR lever 

advisory lights out. 

10. With minimum delay, LANDING GEAR 

lever—DN. Check 3 green gear locked down 

advisory lights illuminate, all amber doors 

open, red gear unlocked and selector lever 

amber advisory lights out. 

11. Items 9 and 10 may be repeated in an 

effort to achieve 3 gear down and locked. 

CAUTION 

Should the LDG GEAR INOP caution light 

illuminate, or loss of no. 2 hydraulic system 

pressure or quantity, or any abnormality in 

landing gear system indication other than 

those associated with the affected main 

landing gear be experienced, see paragraph 

4.21.1 ALTERNATE LANDING GEAR 

EXTENSION.’’

Accomplishing the actions specified in 

paragraph (k) of this AD terminates the 

requirements of this paragraph, and after the 

replacement has been done, the AFM 

limitation may be removed from the AFM. 

Replacement of Uplock Assembly With New 

Replacement Parts and Requirements 

(g) At the later of the times specified in 

paragraph (g)(1) or (g)(2) of this AD: Replace 

the left and right MLG uplock assemblies, P/ 

N 46500–3, with new or overhauled uplock 

assemblies having P/N 46500–3, –5, –7, or –9 

according to a method approved by either the 

Manager, New York Aircraft Certification 

Office (ACO), FAA; or Transport Canada 

Civil Aviation (TCCA) (or its delegated 

agent). Using Tasks 32–31–21–000–801 and 

32–31–21–400–801 of Chapter 32–31–21 of 

Bombardier Q400 Dash 8 Aircraft 

Maintenance Manual (AMM), PSM 1–84–2, is 

one approved method. For any uplock 

assembly having P/N 46500–3, repeat the 

replacement thereafter at intervals not to 

exceed 2,500 flight hours or 3,000 flight 

cycles, whichever occurs earlier. For any 

uplock assembly having P/N 46500–5, do the 

actions required by paragraph (i) of this AD. 

Replacing an uplock assembly with a new or 

overhauled uplock assembly having P/N 

46500–7 or –9 terminates the requirements of 

this paragraph, for that uplock assembly 

only. 

(1) Before the accumulation of 2,500 total 

flight hours or 3,000 total flight cycles on an 

uplock assembly, whichever occurs earlier; 

or 

(2) Within 14 days after April 23, 2002. 

One-Time Inspection of MLG Uplock Rollers 

With Added Inspection Definition 

(h) Within 30 days after April 23, 2002, do 

a general visual inspection of the left and 

right MLG uplock rollers for the presence of 

an inner low friction (black-colored) liner, in 

accordance with the Accomplishment 

Instructions of Bombardier DHC–8 Alert 

Service Bulletin A84–32–15, dated February 

4, 2002; and, before further flight, do the 

actions required by paragraph (h)(1) or (h)(2) 

of this AD. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Corrective Actions 

(1) If a low friction liner is present, 

reinstall the existing uplock roller; or install 

a new uplock roller, P/N 46575–1, having a 

low friction liner; on the shock strut of the 

MLG in accordance with the service bulletin. 

(2) If a low friction liner is not present, 

replace the existing uplock roller with a new 

uplock roller, P/N 46575–1, having a low 

friction liner, on the shock strut of the MLG 

in accordance with the service bulletin. After 

the effective date of this AD, if the low 

friction liner is not present, replace the 

uplock roller in accordance with paragraph 

(i)(2) of this AD. 

Note 2: Bombardier DHC–8 Alert Service 

Bulletin A84–32–15, dated February 4, 2002, 

references Chapter 32–11–01 of Bombardier 

Q400 Dash 8 AMM, PSM 1–84–2, as an 

additional source of service information for 

procedures to replace an MLG uplock roller. 

New Requirements of This AD 

Repetitive Inspections and Replacement if 

Necessary of a Certain Uplock Assembly 

(i) For any MLG uplock assembly having 

P/N 46500–5, do the inspections specified in 

paragraphs (i)(1) and (i)(2) of this AD at the 

later of the following compliance times: 

Before the accumulation of 2,500 total flight 

hours or 3,000 total flight cycles on the 

uplock assembly, whichever occurs first; or 

within 90 days after the effective date of this 

AD. Repeat the inspections thereafter at 

intervals not to exceed 400 flight hours or 

480 flight cycles, whichever occurs first. 

Replacement of an uplock assembly in 

accordance with paragraph (i)(1) of this AD 

terminates the repetitive inspections of 

paragraphs (i)(1) and (i)(2) of this AD, for that 

uplock assembly only. 

(1) Do a detailed dimensional inspection of 

the surface of the uplock hatch lower jaw for 

the presence of a wear groove and measure 

the wear groove depth to an accuracy of 

0.001 inch, according to a method approved 

by either the Manager, New York ACO; or 

TCCA (or its delegated agent). Using Task 

32–31–21–220–801 of the Bombardier Q400 

Dash 8 AMM, PSM 1–84–2, is one approved 


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3350 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 

method. If the groove depth exceeds 0.007 

inch, before further flight, replace the uplock 

assembly with a new or serviceable uplock 

assembly, P/N 46500–7 or –9, according to a 

method approved by either the Manager, 

New York ACO; or TCCA (or its delegated 

agent). Using Tasks 32–31–21–000–801 and 

32–31–21–400–801 of Chapter 32–31–21 of 

the Bombardier Q400 Dash 8 AMM, PSM 1–

84–2, is one approved method. 

(2) Do a general visual inspection of the 

uplock roller, P/N 46575–1, of the MLG 

uplock assembly to ensure that it rotates 

freely. If the uplock roller does not rotate 

freely, before further flight, replace the 

uplock roller with a new uplock roller, P/N 

46575–1, in accordance with Bombardier 

Temporary Revision (TR) 32–191 and 

Bombardier TR 32–192, both dated May 29, 

2006, both to Bombardier Q400 Dash 8 AMM. 

(j) When the information in Bombardier TR 

32–191 and Bombardier TR 32–192, both 

dated May 29, 2006, is included in the AMM, 

the AMM is approved as an acceptable 

method of compliance for the replacement 

specified in paragraph (i)(2) of this AD. 

Optional Terminating Action for AFM 

Revision, Repetitive Replacements, and 

Repetitive Inspections 

(k) Replacing the left and right MLG uplock 

assemblies having P/N 46500–3 or –5 with 

new or overhauled uplock assemblies having 

P/N 46500–7 or –9 according to a method 

approved by either the Manager, New York 

Aircraft Certification Office (ACO), FAA; or 

Transport Canada Civil Aviation (TCCA) (or 

its delegated agent); terminates the 

requirements of paragraphs (f), (g), (h), and (i) 

of this AD, as applicable. Using Tasks 32–31–

21–000–801 and 32–31–21–400–801 of 

Chapter 32–31–21 of Bombardier Q400 Dash 

8 Aircraft Maintenance Manual (AMM), PSM 

1–84–2, is one approved method. After the 

replacements have been done, the AFM 

limitation required by paragraph (f) of this 

AD may be removed from the AFM. 

Alternative Methods of Compliance (AMOCs) 

(l)(1) The Manager, New York ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(3) AMOCs approved previously in 

accordance with AD 2002–08–05, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Related Information 

(m) Canadian airworthiness directive CF–

2002–13R2, dated May 19, 2005, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(n) You must use the service information 

listed in Table 1 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Service information Revision level Date 

Bombardier DHC–8 Alert Service Bulletin A84–32–15 .......................................................................... Original .................. February 4, 2002. 

Bombardier Temporary Revision 32–191 to the Bombardier Q400 Dash 8 Aircraft Maintenance 

Manual.

Original .................. May 29, 2006. 

Bombardier Temporary Revision 32–192 to the Bombardier Q400 Dash 8 Aircraft Maintenance 

Manual.

Original .................. May 29, 2006. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Bombardier Temporary Revision 32–191, 

dated May 29, 2006, to the Bombardier Q400 

Dash 8 Aircraft Maintenance Manual; and 

Bombardier Temporary Revision 32–192, 

dated May 29, 2006, to the Bombardier Q400 

Dash 8 Aircraft Maintenance Manual; in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) On April 23, 2002 (67 FR 19101, April 

18, 2002), the Director of the Federal Register 

approved the incorporation by reference of 

Bombardier DHC–8 Alert Service Bulletin 

A84–32–15, dated February 4, 2002. 

(3) Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 1Y5, 

Canada, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the 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 January 

5, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–909 Filed 1–24–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25889; Directorate 

Identifier 2006–NM–168–AD; Amendment 

39–14902; AD 2007–02–15] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 170 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

EMBRAER Model ERJ 170 airplanes. 

This AD requires replacement of certain 

electrical bonding clamps and attaching 

hardware with new or serviceable parts, 

as applicable, and other specified 

action. This AD results from failure of 

an electrical bonding clamp, used to 

attach the electrical bonding straps to 

the fuel system lines. We are issuing 

this AD to prevent loss of bonding 

protection in the interior of the fuel 

tanks or adjacent areas that, in 

combination with lightning strike, could 

result in a fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD becomes effective 

March 1, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 1, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), P.O. Box 

343—CEP 12.225, Sao Jose dos 

Campos—SP, Brazil, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 


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