29116 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 

terminates the requirements of paragraph (g) 

of this AD. 

Note 4: Guidance on the inspection and 

replacement procedures specified in 

paragraph (l) of this AD can be found in these 

documents as applicable: 

• Airbus A300–600 AMM, Chapter 29–25– 

00, Page Block 301. 

• Airbus A310 AMM, Chapter 29–25–00, 

Page Block 301. 

• Airbus A300 AMM Chapter 29–25–00, 

Page Block 301. 

Alternative Methods of Compliance 

(AMOCs) 

(m) The Manager, International Branch, 

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: Vladimir Ulyanov, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1138; 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. The AMOC 

approval letter must specifically reference 

this AD. 

Related Information 

(n) European Aviation Safety Agency 

(EASA) airworthiness directive 2007–0273, 

dated October 23, 2007, and French 

airworthiness directive F–2005–089, dated 

June 8, 2005, also address the subject of this 

AD. 

Material Incorporated by Reference 

(o) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Mandatory Service Bulletin A300–57–0244 ................................................................................... 02 November 19, 2007. 

Airbus Mandatory Service Bulletin A300–57–6099 ................................................................................... 01 September 3, 2007. 

Airbus Mandatory Service Bulletin A310–57–2086 ................................................................................... 01 September 3, 2007. 

(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 SAS—EAW 

(Airworthiness Office), 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.airwortheas@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 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 May 20, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13146 Filed 6–18–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0261 Directorate 

Identifier 2009–CE–017–AD; Amendment 

39–15943; AD 2009–13–04] 

RIN 2120–AA64 

Airworthiness Directives; Dornier 

Luftfahrt GmbH Models Dornier 228– 

100, Dornier 228–101, Dornier 228–200, 

Dornier 228–201, Dornier 228–202, and 

Dornier 228–212 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Excessive wear on a guide pin of a power 

lever has been detected during inspections. 

The total loss of the pin could cause loss of 

the flight idle stop and lead to inadvertent 

activation of the beta mode in flight. The 

inadvertent activation of beta mode in flight 

can result in loss of control of the airplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

24, 2009. 

On July 24, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Greg 

Davison, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That NPRM was published in the 

Federal Register on April 23, 2009 (74 

FR 18477). That NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Excessive wear on a guide pin of a power 

lever has been detected during inspections. 

The total loss of the pin could cause loss of 

the flight idle stop and lead to inadvertent 

activation of the beta mode in flight. The 

inadvertent activation of beta mode in flight 

can result in loss of control of the airplane. 

For the reasons described above, this new 

EASA Airworthiness Directive (AD) 

introduces a repetitive detailed inspection of 

the guide pins of the power and condition 

levers and requires the replacement of the 

pins that exceed the allowable wear-limits. 


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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 29117 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect 17 

products of U.S. registry. We also 

estimate that it will take about 20 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $10 per 

product. 

Based on these figures, we estimate 

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

to be $27,370 or $1,610 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD Docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2009–13–04 Dornier Luftfahrt GmbH: 

Amendment 39–15943; Docket No. 

FAA–2009–0261; Directorate Identifier 

2009–CE–017–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 24, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Models Dornier 228– 

100, Dornier 228–101, Dornier 228–200, 

Dornier 228–201, Dornier 228–202, and 

Dornier 228–212 airplanes, all serial 

numbers, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 76: Engine Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Excessive wear on a guide pin of a power 

lever has been detected during inspections. 

The total loss of the pin could cause loss of 

the flight idle stop and lead to inadvertent 

activation of the beta mode in flight. The 

inadvertent activation of beta mode in flight 

can result in loss of control of the airplane. 

For the reasons described above, this new 

EASA Airworthiness Directive (AD) 

introduces a repetitive detailed inspection of 

the guide pins of the power and condition 

levers and requires the replacement of the 

pins that exceed the allowable wear-limits. 

Actions and Compliance 

(f) Do the following actions per the 

instructions in RUAG Aerospace Defence 

Technology Dornier 228 Alert Service 

Bulletin ASB–228–279, dated December 19, 

2008: 

(1) Initial Inspection: Unless already done 

within the last 1,200 hours time-in-service 

(TIS) as of July 24, 2009 (the effective date 

of this AD), inspect upon accumulating 9,600 

hours on the guide pins of the power and 

condition levers or within the next 100 hours 

TIS after July 24, 2009 (the effective date of 

this AD), whichever occurs later. 

(2) Repetitive Inspections: Inspect within 

1,200 hours since the last inspection required 

by paragraph (f)(1) of this AD and thereafter 

at intervals not to exceed 1,200 hours TIS. 

(3) Replacement: Replace the guide pins as 

follows: 

(i) Before further flight, after any 

inspection required in paragraphs (f)(1) or 

(f)(2) of this AD, where any guide pin 

exceeds the acceptable wear-limits as defined 

in the service bulletin; and 

(ii) Prior to any required inspection, you 

may install new power and condition levers 

guide pins instead of doing the inspections 

required in this AD. You must then inspect 

or install new pins upon accumulating 9,600 

hours TIS and follow the repetitive 

inspection intervals of this AD if replacement 

is not made. 

Note 1: If the hours TIS of the throttle box 

assembly is unknown, you may use the hours 

TIS of the airplane to determine the 

compliance time for the inspection. 


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29118 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 

FAA AD Differences 

Note 2: 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: Greg Davison, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; 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 EASA AD No.: 2009– 

0031, dated February 18, 2009; and RUAG 

Aerospace Defence Technology Dornier 228 

Alert Service Bulletin ASB–228–279, dated 

December 19, 2008, for related information. 

Material Incorporated by Reference 

(i) You must use RUAG Aerospace Defence 

Technology Dornier 228 Alert Service 

Bulletin ASB–228–279, dated December 19, 

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 RUAG Aerospace Services 

GmbH, Dornier 228 Customer Support, P.O. 

Box 1253, 82231 Wessling, Federal Republic 

of Germany, telephone: +49 (0) 8153–30– 

2280; fax: +49 (0) 8153–30–3030; E-mail: 

custsupport.dorner228@ruag.com; Internet: 

http://www.ruag.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 June 

10, 2009. 

Scott A. Horn, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–14083 Filed 6–18–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0218; Directorate 

Identifier 2009–CE–006–AD; Amendment 

39–15944; AD 2009–13–06] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. PA–23, PA–31, and PA–42 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Piper Aircraft, Inc. (Piper) PA–23 series 

airplanes and all PA–31 and PA–42 

series airplanes. This AD establishes life 

limits for safety-critical nose baggage 

door components. This AD also requires 

you to replace those safety-critical nose 

baggage door components and 

repetitively inspect and lubricate the 

nose baggage door latching mechanism 

and lock assembly. This AD results from 

several incidents and accidents, 

including fatal accidents, where the 

nose baggage door opening in flight was 

listed as a causal factor. We are issuing 

this AD to detect and correct damaged, 

worn, corroded, or non-conforming nose 

baggage door components, which could 

result in the nose baggage door opening 

in flight. The door opening in flight 

could significantly affect the handling 

and performance of the aircraft. It could 

also allow baggage to be ejected from the 

nose baggage compartment and strike 

the propeller. This failure could lead to 

loss of control. 

DATES: This AD becomes effective on 

July 24, 2009. 

On July 24, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: To get the service 

information identified in this AD, 

contact Piper Aircraft, Inc., 2926 Piper 

Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; fax: (772) 

978–6573; Internet: http:// 

www.newpiper.com/company/ 

publications.asp. 

To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590, or on the Internet at http:// 

www.regulations.gov. The docket 

number is FAA–2009–0218; Directorate 

Identifier 2009–CE–006–AD. 

FOR FURTHER INFORMATION CONTACT: 

Gregory K. Noles, Aerospace Engineer, 

One Crown Center, 1895 Phoenix Blvd., 

Suite 450, Atlanta, Georgia 30349; 

telephone: (770) 703–6085; fax: (770) 

703–6097. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 3, 2009, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

certain Piper PA–23 series airplanes and 

all PA–31 and PA–42 series airplanes. 

This proposal was published in the 

Federal Register as a notice of proposed 

rulemaking (NPRM) on March 10, 2009 

(74 FR 10195). The NPRM proposed to 

establish life limits for safety-critical 

nose baggage door components. The 

NPRM also proposed to require 

replacement of those safety-critical nose 

baggage door components and 

repetitively inspect and lubricate the 

nose baggage door latching mechanism 

and lock assembly. 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. The following presents the 

comments received on the proposal and 

FAA’s response to each comment: 

Comment Issue No. 1: Require the 

Installation of a Secondary Forward 

Baggage Door Latch 

Iliamna Air Taxi, Inc. and others 

request the AD incorporate a secondary 

forward baggage door latch per 

supplemental type certificate (STC) 

number SA02331AK as part of the 

solution. The recommendations range 

from making the STC latch an 

additional action to this AD to having 

the STC latch as a terminating action for 

this AD. The commenters suggest the 

STC latch provides a cost-effective 

option that provides additional or 

improved safety to the AD action. One 

commenter questioned the validity of 

the AD action by referencing incidents/ 

accidents that occurred after the FAA 


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