Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations 13681 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the regulation: 

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 an economic evaluation 

of the estimated costs to comply with 

this AD. See the DMS to examine the 

economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2006–26–51 Eurocopter Deutschland 

GmbH: Amendment 39–14961. Docket 

No. FAA–2006–26721; Directorate 

Identifier 2006–SW–28–AD. 

Applicability 

Model MBB–BK 117 C–2 helicopters, serial 

number (S/N) 9075 and higher, and those 

helicopters from S/N 9004 up to and 

including 9074, on which Service Bulletin 

MBB BK117 C–2–67–006 has been 

accomplished, with a tail rotor control lever 

B642M1009103, installed, certificated in any 

category. 

Note 1: The referenced Eurocopter Alert 

Service bulletin MBB BK 117 C–2–67–006, 

dated July 25, 2006, pertains to the subject 

of this AD. That ASB states that it offers 

improvements with regard to a reduction of 

the operational pedal control forces and 

involves two modifications. One of the 

modifications involves installing an 

optimized tail rotor control lever assembly 

‘‘consisting of modified weights and 

modified control lever pre-assys.’’ Installing 

the optimized tail rotor control lever 

assembly, in part, involved replacing the 2 

control levers, part number (P/N) 

B642M1009102, with 2 control levers, P/N 

B642M1009103, and replacing the 4 weights, 

P/N B642M1011201, with 4 weights, P/N 

B642M1011202. 

Compliance 

Required as indicated, unless 

accomplished previously. 

To prevent separation of the tail rotor 

control lever dynamic weights (weights) in 

flight, severe vibration, and subsequent loss 

of control of the helicopter, accomplish the 

following: 

(a) Before further flight, mark the position 

of the weights, remove the split pins, remove 

the weights, and visually inspect the tail 

rotor control lever in the area around the 

split pin bore for score marks, notching, 

scratching, or a crack. Conduct the inspection 

by following the Accomplishment 

Instructions, paragraph 3A(1) and Figure 1 of 

Eurocopter Alert Service Bulletin No. MBB 

BK117 C–2–64A–002, dated December 21, 

2006 (ASB). 

(1) If you find score marks, notching, or 

scratches, that exceed the maintenance 

manual limits, or find a crack, replace the tail 

rotor control lever with an airworthy tail 

rotor control lever before further flight. 

(2) If you do not find score marks, 

notching, scratches, or a crack, within 10 

hours time-in-service (TIS), and thereafter at 

intervals not to exceed 25 hours TIS, repeat 

the visual inspection of the tail rotor control 

lever as described in paragraph (a) of this AD. 

(3) After any repetitive inspection, if you 

find score marks, notching, or scratches, that 

exceed the maintenance manual limits or 

find a crack, replace the tail rotor control 

lever with an airworthy tail rotor control 

lever before further flight. 

(4) Reassemble the tail rotor control lever 

by following the appropriate maintenance 

instructions and the Accomplishment 

Instructions, paragraph 3A(4) and Figure 1 of 

the ASB. 

(b) To request an alternative method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, FAA, ATTN: Charles 

Harrison, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Fort Worth, Texas 

76193–0110, telephone (817) 222–5128, fax 

(817) 222–5961, for information about 

previously approved alternative methods of 

compliance. 

(c) Special flight permits will not be 

issued. 

(d) The inspections and reassembly shall 

be done in accordance with the specified 

portions of Eurocopter Alert Service Bulletin 

No. MBB BK117 C–2–64A–002, dated 

December 21, 2006. The Director of the 

Federal Register approved this incorporation 

by reference in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (972) 

641–3460, fax (972) 641–3527. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 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. 

(e) This amendment becomes effective on 

April 9, 2007, to all persons except those 

persons to whom it was made immediately 

effective by Emergency AD 2006–26–51, 

issued December 22, 2006, which contained 

the requirements of this amendment. 

Note 2: The subject of this AD is addressed 

in Luftfahrt-Bundesamt (Federal Republic of 

Germany) AD D–2006–428, dated December 

22, 2006. 

Issued in Fort Worth, Texas, on March 14, 

2007. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–5139 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–2006–26272; Directorate 

Identifier 2006–NM–153–AD; Amendment 

39–14999; AD 2007–06–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 


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13682 Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations 

Airbus Model A318, A319, A320, and 

A321 airplanes. This AD requires 

repetitive inspections of the operation of 

the main landing gear (MLG) door 

opening sequence to determine if a 

defective actuator is installed, and 

replacing any defective actuator with a 

new actuator. This AD results from 

reports of slow operation of the 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. 

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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; 

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 all Airbus Model A318, A319, 

A320, and A321 airplanes. That NPRM 

was published in the Federal Register 

on December 8, 2006 (71 FR 71101). 

That NPRM proposed to require 

repetitive inspections of the operation of 

the main landing gear (MLG) door 

opening sequence to determine if a 

defective actuator is installed, and to 

replace any defective actuator with a 

new actuator. 

Relevant Service Information 

Since we issued the NPRM, we have 

reviewed Airbus Service Bulletin A320–

32–1309, Revision 01, dated June 19, 

2006. Revision 01 specifies that no 

additional work is necessary for 

airplanes modified by any previous 

issue. We referred to Airbus Service 

Bulletin A320–32–1309, dated March 7, 

2006, in the NPRM for accomplishing 

the specified actions. We have changed 

this AD to refer to Revision 01 of the 

service bulletin for accomplishing the 

specified actions, and to give credit for 

accomplishing the specified actions in 

accordance with the original issue 

before the effective date of this AD. 

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 with the change 

described previously. This change will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we may 

consider further rulemaking then. 

Costs of Compliance 

This AD affects about 700 airplanes of 

U.S. registry. The inspection takes about 

1 work hour per airplane, at an average 

labor rate of $80 per work hour. Based 

on these figures, the estimated cost of 

the AD for U.S. operators is $56,000, or 

$80 per airplane, per inspection cycle. 

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): 

2007–06–18 Airbus: Amendment 39–14999. 

Docket No. FAA–2006–26272; 

Directorate Identifier 2006–NM–153–AD. 

Effective Date 

(a) This AD becomes effective April 27, 

2007. 

Affected ADs 

(b) None. 


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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 


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