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, 29116-29118 [E9-14083]

Download as PDF 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 Airbus Mandatory Service Bulletin A300–57–0244 ................................................................................... Airbus Mandatory Service Bulletin A300–57–6099 ................................................................................... Airbus Mandatory Service Bulletin A310–57–2086 ................................................................................... (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 https:// 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: https://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] cprice-sewell on PRODPC61 with RULES 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. 14:33 Jun 18, 2009 Jkt 217001 02 01 01 November 19, 2007. September 3, 2007. September 3, 2007. 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 https:// 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: 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: Discussion 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. 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. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 24, 2009. VerDate Nov<24>2008 Date PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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: E:\FR\FM\19JNR1.SGM 19JNR1 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 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. cprice-sewell on PRODPC61 with RULES 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 VerDate Nov<24>2008 14:33 Jun 18, 2009 Jkt 217001 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 https:// 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 29117 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. E:\FR\FM\19JNR1.SGM 19JNR1 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. cprice-sewell on PRODPC61 with RULES 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: https://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 VerDate Nov<24>2008 14:33 Jun 18, 2009 Jkt 217001 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: https://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, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978–6573; Internet: https:// 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 https:// 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 E:\FR\FM\19JNR1.SGM 19JNR1

Agencies

[Federal Register Volume 74, Number 117 (Friday, June 19, 2009)]
[Rules and Regulations]
[Pages 29116-29118]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-14083]


-----------------------------------------------------------------------

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 https://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.


[[Page 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 work-hours 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 https://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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:


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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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.


[[Page 29118]]



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: https://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: https://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
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