Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations 13683 

Applicability 

(c) This AD applies to all Airbus Model 

A318, A319, A320, and A321 airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD results from reports of slow 

operation of the main landing gear (MLG) 

door opening/closing sequence due to a 

defective actuator. We are issuing this AD to 

detect and correct defective actuators of the 

MLG door, which could result in slow 

operation of the MLG door and consequent 

non-extension of the MLG during an 

emergency freefall operation. 

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. 

Repetitive Inspections/Replacement 

(f) At the time specified in paragraph (f)(1) 

or (f)(2) of this AD, as applicable: Do a 

general visual inspection of the operation of 

the MLG door opening sequence to determine 

if a defective actuator is installed by doing 

all the applicable actions, including 

replacing the door actuator, as applicable, 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320–

32–1309, Revision 01, dated June 19, 2006. 

Do all applicable replacements before further 

flight. Repeat the inspection thereafter at 

intervals not to exceed 900 flight cycles. 

Accomplishing the actions before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A320–32–1309, 

dated March 7, 2006, is acceptable for 

compliance with the corresponding 

requirements in this paragraph. 

(1) For airplanes on which a record of the 

total number of flight cycles on the MLG door 

actuator is available: Before the accumulation 

of 3,000 total flight cycles on the MLG door 

actuator, or within 800 flight cycles after the 

effective date of this AD, whichever is later. 

(2) For airplanes on which a record of the 

total number of flight cycles on the MLG door 

actuator is not available: Within 800 flight 

cycles after the effective date 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 enhance visual access to 

all exposed 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.’’

No Reporting/Parts Return Required 

(g) Although the Accomplishment 

Instructions of Airbus Service Bulletin A320–

32–1309, Revision 01, dated June 19, 2006, 

specify submitting certain information to the 

manufacturer and sending defective actuators 

back to the component manufacturer for 

investigation, this AD does not include those 

requirements. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 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. 

Related Information 

(i) European Aviation Safety Agency 

airworthiness directive 2006–0112, dated 

May 15, 2006, also addresses the subject of 

this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Service Bulletin 

A320–32–1309, Revision 01, dated June 19, 

2006, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on March 

13, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–5221 Filed 3–22–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26725; Directorate 

Identifier 2006–NM–161–AD; Amendment 

39–15000; AD 2007–06–19] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, and –106 

Airplanes and Model DHC–8–200 and 

DHC–8–300 Series 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 

Bombardier Model DHC–8–102, –103, 

and –106 airplanes and Model DHC–8–

200 and DHC–8–300 series airplanes. 

This AD requires modifying the main 

landing gear (MLG) and nose landing 

gear (NLG) handle assemblies for 

alternate release and the MLG retaining 

plate. This AD also requires doing a 

related investigative action and 

corrective action if necessary. This AD 

results from reports of broken or 

damaged MLG and NLG alternate 

release cables caused by rubbing and 

fraying at the cable-to-handle interface. 

We are issuing this AD to prevent 

breakage of the MLG and NLG alternate 

release cables, which, if the normal gear 

extension fails, could result in the 

inability to extend the MLG or NLG and 

consequent collapse of the landing gear 

during ground maneuvers or upon 

landing. 

DATES: This AD becomes effective April 

27, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 27, 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 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 would 


sroberts on PROD1PC70 with RULES
13684 Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations 

apply to certain Bombardier Model 

DHC–8–102, –103, and –106 airplanes 

and Model DHC–8–200 and DHC–8–300 

series airplanes. That NPRM was 

published in the Federal Register on 

January 8, 2007 (72 FR 662). That NPRM 

proposed to require modifying the main 

landing gear (MLG) and nose landing 

gear handle assemblies for alternate 

release and the MLG retaining plate. 

That NPRM also proposed to require 

doing a related investigative action and 

corrective action if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour 

Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Modification .......................................................................... 5 $80 $400 164 $65,600 

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: 

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

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2007–06–19 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–15000. 

Docket No. FAA–2006–26725; 

Directorate Identifier 2006–NM–161–AD. 

Effective Date 

(a) This AD becomes effective April 27, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–102, DHC–8–103, and DHC–8–106 

airplanes and Model DHC–8–200 and DHC–

8–300 series airplanes; certificated in any 

category; serial numbers 003 through 579 

inclusive. 

Unsafe Condition 

(d) This AD results from reports of broken 

or damaged main landing gear (MLG) and 

nose landing gear (NLG) alternate release 

cables caused by rubbing and fraying at the 

cable-to-handle interface. We are issuing this 

AD to prevent breakage of the MLG and NLG 

alternate release cables, which, if the normal 

gear extension fails, could result in the 

inability to extend the MLG or NLG and 

consequent collapse of the landing gear 

during ground maneuvers or upon landing. 

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. 

Modification 

(f) Within 3,000 flight hours after the 

effective date of this AD, modify the MLG 

and NLG handle assemblies for alternate 

release and the MLG retaining plate, do the 

related investigative action, and the 

corrective action as applicable, by 

accomplishing all the applicable actions 

specified in the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–32–146, Revision ‘D,’ dated February 7, 

2003. Do the corrective action, as applicable, 

before further flight. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(g) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 8–32–146, dated 

September 10, 1999; Revision ‘A,’ dated 

January 17, 2001; Revision ‘B,’ dated June 25, 

2001; or Revision ‘C,’ dated January 24, 2003; 

are considered acceptable for compliance 

with the corresponding action specified in 

this AD. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install any part specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, on any airplane. 

(1) MLG handle assembly, part number (P/ 

N) 83260042. 

(2) NLG handle assembly, P/N 83260020. 

(3) MLG retaining plate, P/N 83260043. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 


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Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations 13685 

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. 

Related Information 

(j) Canadian airworthiness directive CF–

2006–09, issued May 8, 2006, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(k) You must use Bombardier Service 

Bulletin 8–32–146, Revision ‘D,’ dated 

February 7, 2003, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

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 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 

13, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–5217 Filed 3–22–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26595; Directorate 

Identifier 2006–NM–208–AD; Amendment 

39–14998; AD 2007–06–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320 Series 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 

Airbus Model A320 series airplanes. 

This AD requires replacing the carbon 

fiber reinforced plastic (CFRP) actuator 

fittings of the rudder with aluminum 

actuator fittings and doing related 

investigative and corrective actions. 

This AD results from rupture of a CFRP 

actuator fitting during maintenance. We 

are issuing this AD to prevent rupture 

of a rudder actuator fitting, which could 

result in reduced controllability of the 

airplane. 

DATES: This AD becomes effective April 

27, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 27, 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 Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

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 would 

apply to certain Airbus Model A320 

series airplanes. That NPRM was 

published in the Federal Register on 

December 15, 2006 (71 FR 75432). That 

NPRM proposed to require replacing the 

carbon fiber reinforced plastic (CFRP) 

actuator fittings of the rudder with 

aluminum actuator fittings and doing 

related investigative and corrective 

actions. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the NPRM 

Airbus supports the NPRM. 

Request To Revise Discussion Section 

In the Discussion section of the 

NPRM, we stated that investigation 

revealed that the CFRP actuator fittings 

cannot sustain limit loads resulting from 

ground gust conditions due to design of 

the fitting. Airbus requests that we 

revise that statement to clarify that the 

CFRP actuator fittings ‘‘on the rudder 

side’’ cannot sustain limit 

‘‘compression’’ loads resulting from 

ground gust conditions due to design of 

the fitting. We agree with Airbus’

statement. However, we have not 

changed the AD in this regard, since the 

Discussion section is not retained in the 

final rule. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the change described 

previously. We have determined that 

this change will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

This AD affects about 38 airplanes of 

U.S. registry. The required action takes 

about 100 work hours per airplane, at an 

average labor rate of $80 per work hour. 

Required parts cost about $6,310 per 

airplane. Based on these figures, the 

estimated cost of the AD for U.S. 

operators is $543,780, or $14,310 per 

airplane. 

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 


sroberts on PROD1PC70 with RULES