18118 Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations 

Subject 

(d) Air Transport Association of America 

(ATA) Code 30: Ice and Rain Protection. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

This Airworthiness Directive (AD) is 

prompted by some occurrences where the 

Deice Pressure Regulator has vented too 

much hot air into the forward compartment 

damaging the oxygen cylinder ON/OFF cable, 

the Ram-Air Scoop cable and the 

Environmental Control System (ECS) firewall 

shut-off valve cable. 

If incorrectly adjusted, or defective, the 

Deice Pressure Regulator can vent hot air into 

the forward compartment. This situation can 

cause overheating and failures of components 

located inside the forward compartment, 

which could result in potential loss of several 

functions essential for safe flight. 

For the reason described above, this AD 

mandates the installation of a flange and 

scoop in the aircraft skin to vent the hot air 

from the Deice Pressure Regulator overboard. 

Actions and Compliance 

(f) Unless already done, within the next 3 

months after May 26, 2009 (the effective date 

of this AD), install an overboard vent for the 

airfoil deice system pressure regulator 

(Modification Kit Number 500.50.12.332) 

following the Accomplishment Instructions 

in PILATUS AIRCRAFT LTD. PC12 Service 

Bulletin No. 30–011, dated July 9, 2008. 

FAA AD Differences 

Note: 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, Standards Office, 

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: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64016; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No. 2009–0007, 

dated January 13, 2009; and PILATUS 

AIRCRAFT LTD. PC12 Service Bulletin No. 

30–011, dated July 9, 2008, for related 

information. 

Material Incorporated by Reference 

(i) You must use PILATUS AIRCRAFT 

LTD. PC12 Service Bulletin No. 30–011, 

dated July 9, 2008, 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 PILATUS AIRCRAFT LTD., 

Customer Service Manager, CH–6371 

STANS, Switzerland; telephone: +41 (0)41 

619 62 08; fax: +41 (0)41 619 73 11; Internet: 

http://www.pilatus-aircraft.com/, or e-mail: 

SupportPC12@pilatus-aircraft.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on April 

9, 2009. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–8687 Filed 4–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0360; Directorate 

Identifier 2009–NM–039–AD; Amendment 

39–15887; AD 2009–09–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320 and A321 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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: 

During a routine inspection on an Airbus 

A321 aircraft, the operator discovered that a 

bearing of the flap track No. 1 pendulum 

assembly had migrated out of position. * * * 

This condition, if not corrected, could lead 

to separation of the bearing/flap track 

assembly, resulting in the detachment of the 

affected flap surface from the wing and 

consequent loss of control of the aircraft. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

6, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 6, 2009. 

We must receive comments on this 

AD by May 21, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

mstockstill on PROD1PC66 with RULES

Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations 18119 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA) which is the Technical Agent of 

the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0025, 

dated February 10, 2009 [Corrected 

February 11, 2009] (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During a routine inspection on an Airbus 

A321 aircraft, the operator discovered that a 

bearing of the flap track No. 1 pendulum 

assembly had migrated out of position. The 

investigation has confirmed that the 

pendulum bearing migration was probably 

due to the methods used during in-service 

replacement of the bearing during 

maintenance, whereby the necessary special 

tools, fixtures and equipment were not used. 

This condition, if not corrected, could lead 

to separation of the bearing/flap track 

assembly, resulting in the detachment of the 

affected flap surface from the wing and 

consequent loss of control of the aircraft. 

For the reasons described above, this AD 

requires a one-time inspection of the affected 

flap track No.1 pendulum assembly for 

bearing migration and, in case any bearing is 

found to have migrated, the replacement of 

the affected flap track pendulum assembly. 

Note: Based on this in-service experience, 

showing the potential safety effect of not 

following the TC Holder’s accomplishment 

instructions, Airbus has removed the 

instructions to replace the bearing in the 

pendulum assembly from the A320 Family 

aircraft maintenance documentation. 

Component Maintenance Manual (CMM) 

references are 27–54–43 for the A318, A319 

and A320, and 27–54–42 for the A321. 

If no migration is found during the onetime inspection for migration, the 

required actions include an inspection 

for correct swaging of the spherical 

bearing in the No.1 flap track pendulum 

assembly. If the bearing is found 

incorrectly swaged, the corrective 

actions include contacting Airbus for 

repair instructions and doing the repair. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–57–1144, including Appendix 01, 

Revision 01, dated June 18, 2007; and 

Service Bulletin A320–57A1146, 

including Appendix 01, dated 

September 21, 2007. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the 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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because of the possible separation 

of the bearing and flap track assembly, 

resulting in the detachment of the 

affected flap surface from the wing and 

consequent loss of control of the 

airplane. Therefore, we determined that 

notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0360; 

Directorate Identifier 2009–NM–039– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

mstockstill on PROD1PC66 with RULES

18120 Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations 

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: 

2009–09–01 Airbus: Amendment 39–15887. 

Docket No. FAA–2009–0360; Directorate 

Identifier 2009–NM–039–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 6, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318– 

111, A318–112, A318–121, A318–122, A319– 

111, A319–112, A319–113, A319–114, A319– 

115, A319–131, A319–132, A319–133, A320– 

111, A320–211, A320–212, A320–214, A320– 

231, A320–232, A320–233, A321–111, A321– 

112, A321–131, A321–211, A321–212, A321– 

213, A321–231, and A321–232 airplanes; 

certificated in any category; except airplanes 

identified in paragraph (c)(1), (c)(2), (c)(3), or 

(c)(4) of this AD. 

(1) Any airplane for which the date of 

issuance of the original French or German 

airworthiness certificate or the date of 

issuance of the original French or German 

export certificate of airworthiness, is after 

February 24, 2009 (the effective date of 

European Aviation Safety Agency (EASA) 

Airworthiness Directive 2009–0025 

[Corrected: February 11, 2009]). 

(2) Any airplane for which it can be 

positively determined from records review 

that the bearing of any pendulum assembly 

has not been replaced or re-swaged since the 

date of issuance of the original French or 

German airworthiness certificate or the date 

of issuance of the original French or German 

export certificate of airworthiness. 

(3) Any airplane inspected prior to the 

effective date of this AD in accordance with 

Airbus Service Bulletin A320–57A1146, 

dated September 21, 2007 (for Model A318, 

A319 and A320 series airplanes); or in 

accordance with Airbus Service Bulletin 

A320–57A1144, dated February 6, 2007, or 

A320–57–1144, Revision 01, dated June 18, 

2007 (for Model A321 series airplanes), and 

on which it can be positively determined 

from a records review that thereafter no 

replacement with a pendulum assembly 

whose bearing has been replaced or reswaged since new manufacture was 

performed. 

(4) Any airplane inspected prior to the 

effective date of this AD in accordance with 

Airbus Service Bulletin A320–57A1146, 

dated September 21, 2007 (for Model A318, 

A319 and A320 series airplanes); or in 

accordance with Airbus Service Bulletin 

A320–57A1144, dated February 6, 2007, or 

A320–57–1144, Revision 01, dated June 18, 

2007 (for Model A321 series airplanes), and 

on which it can be positively determined 

from a records review that thereafter no 

pendulum bearing replacement or re-swaging 

was performed. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

During a routine inspection on an Airbus 

A321 aircraft, the operator discovered that a 

bearing of the flap track No.1 pendulum 

assembly had migrated out of position. The 

investigation has confirmed that the 

pendulum bearing migration was probably 

due to the methods used during in-service 

replacement of the bearing during 

maintenance, whereby the necessary special 

tools, fixtures and equipment were not used. 

This condition, if not corrected, could lead 

to separation of the bearing/flap track 

assembly, resulting in the detachment of the 

affected flap surface from the wing and 

consequent loss of control of the aircraft. 

For the reasons described above, this AD 

requires a one-time inspection of the affected 

flap track No.1 pendulum assembly for 

bearing migration and, in case any bearing is 

found to have migrated, the replacement of 

the affected flap track pendulum assembly. 

Note: Based on this in-service experience, 

showing the potential safety effect of not 

following the TC Holder’s accomplishment 

instructions, Airbus has removed the 

instructions to replace the bearing in the 

pendulum assembly from the A320 Family 

aircraft maintenance documentation. 

Component Maintenance Manual (CMM) 

references are 27–54–43 for the A318, A319 

and A320, and 27–54–42 for the A321. 

If no migration is found during the one-time 

inspection for migration, the required actions 

include an inspection for correct swaging of 

the spherical bearing in the No.1 flap track 

pendulum assembly. If the bearing is found 

incorrectly swaged, the corrective actions 

include contacting Airbus for repair 

instructions and doing the repair. You may 

obtain further information by examining the 

MCAI in the AD docket. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 600 flight hours after the 

effective date of this AD, inspect for 

migration, and correct swaging as applicable, 

of the pendulum assembly of flap track 

number 1 in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57A1146, dated 

September 21, 2007 (for Model A318, A319 

and A320 series airplanes); or in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1144, 

Revision 01, dated June 18, 2007 (for Model 

A321 series airplanes). 

(i) If the bearing of the pendulum assembly 

of flap track number 1 is found to have 

migrated, before further flight, replace the 

affected pendulum assembly with a new 

pendulum assembly, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57A1146, dated 

September 21, 2007 (for Model A318, A319 

and A320 series airplanes); or in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1144, 

Revision 01, dated June 18, 2007 (for Model 

A321 series airplanes). 

(ii) If the bearing of the pendulum 

assembly of flap track number 1 is incorrectly 

swaged, before further flight, contact Airbus 

for repair instructions and accomplish the 

repair. 

(2) After the effective date of this AD, no 

person shall replace the bearing in the 

pendulum assembly of the flap track or 

install a pendulum assembly, unless: 

(i) The pendulum assembly is of new 

manufacture, or 

(ii) It can be positively determined from a 

records review that the bearing of the 

pendulum assembly has not been replaced or 

re-swaged since new. 

(3) Accomplishment of the actions required 

by paragraph (f)(1), (f)(2), and (f)(3) of this 

AD, before the effective date of this AD in 

accordance with Airbus Service Bulletin 

A320–57A1144, dated February 6, 2007, is 

acceptable for compliance with the 

corresponding requirements of paragraph (f) 

of this AD for Airbus Model A321 series 

airplanes. 

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, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; fax (425) 227–1149. 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 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, 

mstockstill on PROD1PC66 with RULES

Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations 18121 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0025, dated February 10, 2009; Airbus 

Service Bulletin A320–57–1144, Revision 01, 

dated June 18, 2007; and Airbus Service 

Bulletin A320–57A1146, dated September 

21, 2007, for related information. 

Material Incorporated by Reference 

(i) You must use Airbus Service Bulletin 

A320–57A1146, including Appendix 01, 

dated September 21, 2007; or Airbus Service 

Bulletin A320–57–1144, including Appendix 

01, Revision 01, dated June 18, 2007; 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 Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@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. 

Issued in Renton, Washington, on April 8, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–8982 Filed 4–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0361; Directorate 

Identifier 2009–NM–046–AD; Amendment 

39–15888; AD 2009–09–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–400 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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: 

Several reports have been received on 

failures of the aft hinge of the main landing 

gear (MLG) forward stabilizer brace. 

Laboratory examinations have found that the 

fatigue cracks were initiated from the dowel 

pin hole at the aft hinge lug of the MLG 

forward stabilizer brace where the stop 

bracket is attached. Failure of the stabilizer 

brace could result in the collapse of the main 

landing gear. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

6, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 6, 2009. 

We must receive comments on this 

AD by May 21, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Jon 

Hjelm, Aerospace Engineer, Airframe 

and Propulsion Branch, ANE–171, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7323; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Emergency Airworthiness Directive CF– 

2009–11, dated March 13, 2009 (referred 

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

an unsafe condition for the specified 

products. The MCAI states: 

Several reports have been received on 

failures of the aft hinge of the main landing 

gear (MLG) forward stabilizer brace. 

Laboratory examinations have found that the 

fatigue cracks were initiated from the dowel 

pin hole at the aft hinge lug of the MLG 

forward stabilizer brace where the stop 

bracket is attached. Failure of the stabilizer 

brace could result in the collapse of the main 

landing gear. 

Required actions include inspections for 

damage (including excessive wear, 

corrosion, foreign object damage, and 

cracking) of the MLG forward stabilizer 

brace assemblies and applicable 

corrective actions. The inspections 

include the following inspections: 

• A visual inspection for evidence of 

excessive wear on the outside diameter 

of apex pins part number 46418–1. 

• A visual inspection for damage 

(including cracking, corrosion, and 

foreign object damage) of the face of the 

forward stabilizer brace lugs, stop 

bracket retention hole apex bushings, 

and stop bracket. 

• An inspection to detect 0.050-inchlong exposed surface cracks around the 

stop bracket mounting face and 

retention pin hole areas, using either of 

the following nondestructive inspection 

methods: (1) An eddy current 

inspection, or (2) a visual inspection 

using liquid penetrant under 10X 

magnification. 

The applicable corrective actions 

include the following: 

• Contacting Goodrich for repair 

instructions and doing the repair. 

• Replacing the stop bracket. 

• Reworking the forward stabilizer 

brace assembly. 

• Replacing the forward stabilizer 

brace assembly. 

The required actions also include, for 

certain airplanes, repetitive detailed 

visual inspection for cracking of both 

MLG forward stabilizer braces, 

including liquid penetrant inspections 

for cracking if necessary, and repair of 

the cracking if necessary. The required 

actions also include, for certain 

airplanes, a detailed visual inspection 

mstockstill on PROD1PC66 with RULES