Airworthiness Directives; Fokker Model F.28 Mark 0100 Airplanes, 30914-30917 [E9-14676]

Download as PDF 30914 Federal Register / Vol. 74, No. 123 / Monday, June 29, 2009 / Rules and Regulations 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. 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: cprice-sewell on PRODPC61 with RULES ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ VerDate Nov<24>2008 15:24 Jun 26, 2009 Jkt 217001 2009–13–09 Microturbo SA: Amendment 39–15948.; Docket No. FAA–2009–0510; Directorate Identifier 2009–NE–16–AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 14, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Microturbo SA Saphir 2 model 016 auxiliary power units (APUs) on which the exhaust thermal insulation has been replaced since January 1, 1995. These APUs are installed on, but not limited to, Dassault Falcon 20 airplanes. Reason (d) European Aviation Safety Agency (EASA) AD No. 2009–0100, dated May 4, 2009, states: Due to a lapse in manufacturing quality control, the exhaust thermal insulation of certain Microturbo SA Saphir 2 model 016 APUs may not meet the approved design standard, and may fail in service. The affected part numbers are 016–33–01 (Inner Thermal Insulation), 016–33–02 (Outer Thermal Insulation), and 016–33–03 (EGT Sensor Thermal Insulation). This condition, if not corrected, could result in rapid deterioration and physical breakdown of the exhaust thermal insulation, leading to loss of insulation efficiency and ultimately exposure of the hot APU exhaust section and risk of fire. We are issuing this AD to prevent rapid deterioration and physical breakdown of the exhaust thermal insulation, leading to loss of insulation efficiency and ultimately exposure of the hot APU exhaust section and risk of fire. Actions and Compliance (e) Unless already done, do the following actions. Initial and Repetitive Inspections (1) Within 10 APU operating hours from the effective date of this AD, visually inspect the exhaust thermal insulation for signs of deterioration. Repeat the inspection at intervals not exceeding 10 operating APU hours. (2) If deterioration is detected, replace the exhaust thermal insulation before operating the APU again. Use paragraphs 2.A. through 2.C.(4)(b) of Microturbo SA Alert Service Bulletin No. 49–11A76, Revision 1, dated September 6, 2007, to do the replacement. Alternative Methods of Compliance (AMOCs) (g) The Manager, Boston Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2009–0100, dated May 4, 2009, for related information. (i) Contact Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: michaelschwetz@faa.gov; telephone (781) 238–7761; fax (781) 238– 7170, for more information about this AD. Material Incorporated by Reference (j) You must use Microturbo SA Alert Service Bulletin No. 49–11A76, Revision 1, dated September 6, 2007, 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 Microturbo SA, Technical Publications Department, 8, Chemin du pont de Rupe, BP 62089, 31019 Toulouse Cedex 2, France; telephone (33) (0)5 61 37 55 00; fax (33) (0)5 61 70 74 45. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on June 17, 2009. Carlos Pestana, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–14809 Filed 6–26–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0198; Directorate Identifier 2008–NM–129–AD; Amendment 39–15941; AD 2009–13–02] Mandatory Terminating Action (3) As mandatory terminating action to the repetitive visual inspections required by this AD, replace the exhaust thermal insulation within 50 APU operating hours from the effective date of this AD. Use paragraphs 2.A. through 2.C.(4)(b) of Microturbo SA Alert Service Bulletin No. 49–11A76, Revision 1, dated September 6, 2007, to do the replacement. AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. FAA AD Differences (f) None. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 RIN 2120-AA64 Airworthiness Directives; Fokker Model F.28 Mark 0100 Airplanes E:\FR\FM\29JNR1.SGM 29JNR1 30915 Federal Register / Vol. 74, No. 123 / Monday, June 29, 2009 / Rules and Regulations which applies to certain Fokker Model F.28 Mark 0100 airplanes. That AD currently requires revisions to the airplane flight manual (AFM) to include procedures to prohibit use of reverse engine thrust power settings between idle and emergency maximum and to prohibit stabilized engine operation in a certain engine speed range on the ground. This new AD continues to require revising the AFM to include certain procedures. This AD also requires removing the normal maximum (second) detent for the reverse-thrust control. In addition, this AD requires revising the AFM to prohibit use of reverse thrust in flight and to limit operation of Max Reverse thrust. This AD results from issuance of mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to prevent inadvertent operation in the prohibited stabilized engine speed range on the ground, which could result in uncontained engine fan blade failure due to high cycle fatigue cracking. DATES: This AD becomes effective August 3, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 3, 2009. ADDRESSES: For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252– 627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices@ stork.com; Internet https:// www.myfokkerfleet.com. You may review copies of the referenced 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. 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 this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 98–06–07, amendment 39–10384 (63 FR 11985, March 12, 1998). The existing AD applies to certain Fokker Model F.28 Mark 0100 airplanes. That NPRM was published in the Federal Register on March 6, 2009 (74 FR 9774). That NPRM proposed to continue to require revising the AFM to include procedures prohibiting stabilized engine operation in a certain engine speed range on the ground. That NPRM also proposed to require removing the normal maximum (second) detent for the reverse-thrust control. In addition, that NPRM proposed to revise the AFM to prohibit use of reverse thrust in flight and to limit operation of Max Reverse thrust. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours AFM revision (required by AD 98–06–07) ............................................... Removal of second detent (new action) .................................................. AFM revision (new action) ....................................................................... 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 VerDate Nov<24>2008 15:24 Jun 26, 2009 Jkt 217001 Average labor rate per hour 1 3 1 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 $80 80 80 Cost per airplane $80 240 80 Number of U.S.-registered airplanes 5 5 5 Fleet cost $400 1,200 400 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. E:\FR\FM\29JNR1.SGM 29JNR1 30916 Federal Register / Vol. 74, No. 123 / Monday, June 29, 2009 / Rules and Regulations 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 PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–10384 (63 FR 11985, March 12, 1998) and by adding the following new airworthiness directive (AD): ■ 2009–13–02 Fokker Services B.V.: Amendment 39–15941. Docket No. FAA–2009–0198; Directorate Identifier 2008–NM–129–AD. Effective Date (a) This AD becomes effective August 3, 2009. Affected ADs (b) This AD supersedes AD 98–06–07. Applicability (c) This AD applies to Fokker Model F.28 Mark 0100 airplanes, certificated in any category, equipped with Rolls-Royce (RR) TAY 650–15 engines. cprice-sewell on PRODPC61 with RULES Subject (d) Air Transport Association (ATA) of America Code 76: Engine controls. Unsafe Condition (e) This AD results from issuance of mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to prevent inadvertent operation in the prohibited stabilized engine speed range on the ground, which could result in uncontained engine fan blade failure due to high cycle fatigue cracking. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Jkt 217001 ‘‘LIMITATIONS POWERPLANT and APU LIMITATIONS THRUST REVERSER 1. The authority citation for part 39 continues to read as follows: ■ 15:24 Jun 26, 2009 (g) Within 72 hours after March 27, 1998 (the effective date of AD 98–06–07), revise the Limitations Section of the FAA-approved AFM to add the following. This may be accomplished by inserting a copy of this AD in the AFM. • To avoid high fan blade stresses, stabilized operation in the speed range between 60% and 75% Low Pressure Rotational Speed (N1) is not permitted during Ground Operations in Forward or Reverse Thrust, except that passing through this range while increasing or decreasing thrust is permitted. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: VerDate Nov<24>2008 Airplane Flight Manual (AFM) Revision OPERATING LIMITS ■ § 39.13 Certain Requirement of AD 98–06–07 Thrust reversers are intended for ground use only. Intentional use of reverse thrust in flight is prohibited. After reverse thrust has been initiated, a full stop landing must be made. Maximum Reverse Thrust Lever Positions Normal Operation: —The idle detent position shall not be exceeded in normal operation. —Momentarily exceeding the idle detent position, while selecting idle reverse, is acceptable. Emergency Operation: —In case of emergency, the emergency maximum reverse thrust may be used. —If directional control problems occur, reduce to idle reverse or select forward idle. —Stabilized operation with the reverse lever in an intermediate position between idle reverse and emergency maximum reverse is prohibited, except (where approved) during Power-Back operations.’’ Note 1: Fokker Services Manual Change Notification—Operational Documentation (MCNO) No. F100–006, dated November 27, 1997, contains information that pertains to this subject. Rolls-Royce PLC Engine Operating Instruction Manual Reference F– TAY–3RR, revised by transmittal letter No. 13, dated October 15, 1997, also pertains to this subject. New Actions Required by This AD Removal of Normal Maximum Detent (h) Within 12 months after the effective date of this AD, remove the normal maximum (second) detent for the reversethrust control, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–76–014, Revision 2, dated December 12, 2007. Accomplishing the removal terminates the requirements of paragraph (g) of this AD. (i) Actions done before the effective date of this AD in accordance with Fokker Service Bulletin SBF100–76–014, dated October 1, 2001; or Revision 1, dated June 1, 2002; are acceptable for compliance with the requirements of paragraph (h) of this AD. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 AFM Revision (j) Concurrently with the requirements of paragraph (h) of this AD, revise the Limitations Section of the Fokker F.28 Mark 0100 AFM to include the following (this may be accomplished by inserting a copy of this AD into the AFM): ‘‘THRUST REVERSERS Thrust reversers are intended for ground use only. Intentional use of reverse thrust in flight is prohibited. The use of Max Reverse thrust is limited to operations on short runways or on runways with a reduced runway surface friction coefficient or in emergency conditions. Max Reverse thrust shall not be used at airspeeds below 60 knots except in emergency conditions. Reverse thrust selections between Idle Reverse thrust and Max Reverse thrust are prohibited.’’ Note 2: Fokker Manual Change Notification—Operational Documentation (MCNO) F100–032, Revision 1, dated September 21, 2007, contains information related to the AFM revision required by paragraph (j) of this AD. Alternative Methods of Compliance (AMOCs) (k) 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1137; 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. Related Information (l) European Aviation Safety Agency Airworthiness Directive 2008–0089, dated May 13, 2008, also addresses the subject of this AD. Material Incorporated by Reference (m) You must use Fokker Service Bulletin SBF100–76–014, Revision 2, dated December 12, 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 Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252–627–350; fax +31 (0)252–627–211; e-mail technicalservices.fokkerservices@stork.com; Internet https://www.myfokkerfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, E:\FR\FM\29JNR1.SGM 29JNR1 Federal Register / Vol. 74, No. 123 / Monday, June 29, 2009 / Rules and Regulations 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 16, 2009. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–14676 Filed 6–26–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22039; Directorate Identifier 2005–NE–33–AD; Amendment 39– 15950; AD 2009–14–01] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines cprice-sewell on PRODPC61 with RULES AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Turbomeca S.A. Arrius 2F turboshaft engines that have not incorporated Turbomeca Modification Tf75. That AD currently requires replacing the O-ring on the check valve piston in the lubrication unit at repetitive intervals. This AD requires the same repetitive replacements and would require incorporating Modification Tf75 as terminating action to the repetitive Oring replacements. Modification Tf75 replaces the check valve piston with a piston design not requiring an O-ring. This AD results from the European Aviation Safety Agency (EASA) and Turbomeca S.A. mandating the incorporation of Modification Tf75. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, which could result in a forced autorotation landing and damage to the helicopter. DATES: This AD becomes effective August 3, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of August 3, 2009. VerDate Nov<24>2008 15:24 Jun 26, 2009 Jkt 217001 You can get the service information identified in this AD from Turbomeca S.A., 40220 Tarnos, France; e-mail: noria-dallas@turbomeca.com; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, or go to: https:// www.turbomeca-support.com. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by superseding AD 2005–17–17R1, Amendment 39–14940 (72 FR 6925, February 14, 2007), with a proposed AD. The proposed AD applies to Turbomeca S.A. Arrius 2F turboshaft engines that have not incorporated Turbomeca Modification Tf75. We published the proposed AD in the Federal Register on January 22, 2009 (74 FR 3978). That action proposed to require replacing the O-ring on the check valve piston in the lubrication unit at repetitive intervals and to require incorporating Modification Tf75 as terminating action to the repetitive O-ring replacements. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. Change to the Mandatory Terminating Action Compliance Time Since we issued the proposed AD, we realized that there is no direct relationship between the mandatory terminating action compliance date in the proposed AD and the usage rate of PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 30917 the affected helicopters. We changed the AD to require the terminating action be done within 150 flight hours after the effective date of this AD. 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. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 94 Arrius 2F turboshaft engines installed on helicopters of U.S. registry. We also estimate that it will take about one work-hour per engine to perform an O-ring replacement, and about one work-hour to incorporate Modification Tf75. The average labor rate is $80 per work-hour. Required parts will cost about $16 per engine for O-ring replacement, and about $20 per engine for incorporating Modification Tf75. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $18,424. 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. E:\FR\FM\29JNR1.SGM 29JNR1

Agencies

[Federal Register Volume 74, Number 123 (Monday, June 29, 2009)]
[Rules and Regulations]
[Pages 30914-30917]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-14676]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0198; Directorate Identifier 2008-NM-129-AD; 
Amendment 39-15941; AD 2009-13-02]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0100 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD),

[[Page 30915]]

which applies to certain Fokker Model F.28 Mark 0100 airplanes. That AD 
currently requires revisions to the airplane flight manual (AFM) to 
include procedures to prohibit use of reverse engine thrust power 
settings between idle and emergency maximum and to prohibit stabilized 
engine operation in a certain engine speed range on the ground. This 
new AD continues to require revising the AFM to include certain 
procedures. This AD also requires removing the normal maximum (second) 
detent for the reverse-thrust control. In addition, this AD requires 
revising the AFM to prohibit use of reverse thrust in flight and to 
limit operation of Max Reverse thrust. This AD results from issuance of 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country to identify and correct an unsafe 
condition on an aviation product. We are issuing this AD to prevent 
inadvertent operation in the prohibited stabilized engine speed range 
on the ground, which could result in uncontained engine fan blade 
failure due to high cycle fatigue cracking.

DATES: This AD becomes effective August 3, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of August 3, 
2009.

ADDRESSES: For service information identified in this AD, contact 
Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE 
Nieuw-Vennep, the Netherlands; telephone +31 (0)252-627-350; fax +31 
(0)252-627-211; e-mail technicalservices.fokkerservices@stork.com; 
Internet https://www.myfokkerfleet.com. You may review copies of the 
referenced 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.

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 this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 98-06-07, amendment 39-
10384 (63 FR 11985, March 12, 1998). The existing AD applies to certain 
Fokker Model F.28 Mark 0100 airplanes. That NPRM was published in the 
Federal Register on March 6, 2009 (74 FR 9774). That NPRM proposed to 
continue to require revising the AFM to include procedures prohibiting 
stabilized engine operation in a certain engine speed range on the 
ground. That NPRM also proposed to require removing the normal maximum 
(second) detent for the reverse-thrust control. In addition, that NPRM 
proposed to revise the AFM to prohibit use of reverse thrust in flight 
and to limit operation of Max Reverse thrust.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number of
                                                                Average      Cost per      U.S.-
                     Action                       Work hours   labor rate    airplane    registered   Fleet cost
                                                                per hour                 airplanes
----------------------------------------------------------------------------------------------------------------
AFM revision (required by AD 98-06-07).........            1          $80          $80            5         $400
Removal of second detent (new action)..........            3           80          240            5        1,200
AFM revision (new action)......................            1           80           80            5          400
----------------------------------------------------------------------------------------------------------------

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.

[[Page 30916]]

    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

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10384 (63 FR 11985, March 12, 1998) and by adding 
the following new airworthiness directive (AD):

2009-13-02 Fokker Services B.V.: Amendment 39-15941. Docket No. FAA-
2009-0198; Directorate Identifier 2008-NM-129-AD.

Effective Date

    (a) This AD becomes effective August 3, 2009.

Affected ADs

    (b) This AD supersedes AD 98-06-07.

Applicability

    (c) This AD applies to Fokker Model F.28 Mark 0100 airplanes, 
certificated in any category, equipped with Rolls-Royce (RR) TAY 
650-15 engines.

Subject

    (d) Air Transport Association (ATA) of America Code 76: Engine 
controls.

Unsafe Condition

    (e) This AD results from issuance of mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority 
of another country to identify and correct an unsafe condition on an 
aviation product. We are issuing this AD to prevent inadvertent 
operation in the prohibited stabilized engine speed range on the 
ground, which could result in uncontained engine fan blade failure 
due to high cycle fatigue cracking.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Certain Requirement of AD 98-06-07

Airplane Flight Manual (AFM) Revision

    (g) Within 72 hours after March 27, 1998 (the effective date of 
AD 98-06-07), revise the Limitations Section of the FAA-approved AFM 
to add the following. This may be accomplished by inserting a copy 
of this AD in the AFM.

``LIMITATIONS POWERPLANT and APU LIMITATIONS

OPERATING LIMITS

     To avoid high fan blade stresses, stabilized operation 
in the speed range between 60% and 75% Low Pressure Rotational Speed 
(N1) is not permitted during Ground Operations in Forward or Reverse 
Thrust, except that passing through this range while increasing or 
decreasing thrust is permitted.

THRUST REVERSER

    Thrust reversers are intended for ground use only. Intentional 
use of reverse thrust in flight is prohibited. After reverse thrust 
has been initiated, a full stop landing must be made.

Maximum Reverse Thrust Lever Positions

    Normal Operation:
--The idle detent position shall not be exceeded in normal 
operation.
--Momentarily exceeding the idle detent position, while selecting 
idle reverse, is acceptable.

    Emergency Operation:
--In case of emergency, the emergency maximum reverse thrust may be 
used.
--If directional control problems occur, reduce to idle reverse or 
select forward idle.
--Stabilized operation with the reverse lever in an intermediate 
position between idle reverse and emergency maximum reverse is 
prohibited, except (where approved) during Power-Back operations.''

    Note 1: Fokker Services Manual Change Notification--Operational 
Documentation (MCNO) No. F100-006, dated November 27, 1997, contains 
information that pertains to this subject. Rolls-Royce PLC Engine 
Operating Instruction Manual Reference F-TAY-3RR, revised by 
transmittal letter No. 13, dated October 15, 1997, also pertains to 
this subject.

New Actions Required by This AD

Removal of Normal Maximum Detent

    (h) Within 12 months after the effective date of this AD, remove 
the normal maximum (second) detent for the reverse-thrust control, 
in accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-76-014, Revision 2, dated December 12, 2007. 
Accomplishing the removal terminates the requirements of paragraph 
(g) of this AD.
    (i) Actions done before the effective date of this AD in 
accordance with Fokker Service Bulletin SBF100-76-014, dated October 
1, 2001; or Revision 1, dated June 1, 2002; are acceptable for 
compliance with the requirements of paragraph (h) of this AD.

AFM Revision

    (j) Concurrently with the requirements of paragraph (h) of this 
AD, revise the Limitations Section of the Fokker F.28 Mark 0100 AFM 
to include the following (this may be accomplished by inserting a 
copy of this AD into the AFM):

``THRUST REVERSERS

    Thrust reversers are intended for ground use only. Intentional 
use of reverse thrust in flight is prohibited.
    The use of Max Reverse thrust is limited to operations on short 
runways or on runways with a reduced runway surface friction 
coefficient or in emergency conditions. Max Reverse thrust shall not 
be used at airspeeds below 60 knots except in emergency conditions.
    Reverse thrust selections between Idle Reverse thrust and Max 
Reverse thrust are prohibited.''

    Note 2: Fokker Manual Change Notification--Operational 
Documentation (MCNO) F100-032, Revision 1, dated September 21, 2007, 
contains information related to the AFM revision required by 
paragraph (j) of this AD.

Alternative Methods of Compliance (AMOCs)

    (k) 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-1137; 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.

Related Information

    (l) European Aviation Safety Agency Airworthiness Directive 
2008-0089, dated May 13, 2008, also addresses the subject of this 
AD.

Material Incorporated by Reference

    (m) You must use Fokker Service Bulletin SBF100-76-014, Revision 
2, dated December 12, 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 
Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 
AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252-627-350; fax 
+31 (0)252-627-211; e-mail 
technicalservices.fokkerservices@stork.com; Internet https://www.myfokkerfleet.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,

[[Page 30917]]

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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on June 16, 2009.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-14676 Filed 6-26-09; 8:45 am]
BILLING CODE 4910-13-P
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