Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Series Airplanes, 17342-17345 [05-6759]

Download as PDF 17342 Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules 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 airworthiness directive (AD): Airbus: Docket No. FAA–2005–20867; Directorate Identifier 2004–NM–188–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by May 6, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes (collectively called A300–600 airplanes); certificated in any category; having serial numbers 0812, 0813, 0815 through 0818 inclusive, 0821 through 0828 inclusive, and 0836 through 0838 inclusive. Unsafe Condition (d) This AD was prompted by reports of holes in the ram air turbine (RAT) hub. We are issuing this AD to prevent a hole in the RAT hub cover. A hole in the RAT hub cover could allow water to enter the RAT governing mechanism, freeze during flight, and jam the governing mechanism. In addition, the metal particles that result from chafing between the hydraulic flexible hose and the RAT could mix with the lubricant grease and degrade the governing mechanism. In an emergency, a jammed or degraded RAT could result in failure of RAT deployment, loss of hydraulic pressure or electrical power to the airplane, and consequent reduced controllability of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection and Related Investigative/ Corrective Actions (f) Within 2,500 flight hours after the effective date of this AD: Do a one-time detailed inspection for evidence of chafing between the hydraulic flexible hose and the RAT hub, and any applicable related investigative and corrective actions, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A300– 29–6054, Revision 01, excluding Appendix 01, dated November 4, 2004. Any applicable corrective actions must be accomplished before further flight. Although the service bulletin specifies to submit certain information to the manufacturer, and to submit damaged RAMs to the vendor or a repair station, this AD does not include those requirements. VerDate jul<14>2003 17:48 Apr 05, 2005 Jkt 205001 Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Actions Accomplished Previously (g) Actions accomplished before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–29–6054, excluding Appendix 01, dated June 8, 2004, are acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) (h) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (i) French airworthiness directive F–2004– 133, dated August 4, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on March 25, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6758 Filed 4–5–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20870; Directorate Identifier 2004–NM–180–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 series airplanes. This proposed AD would require repetitive inspections for damage of the drive rod assembly of the aileron tab on each aileron actuator; repetitive measurements of the clearance between the aileron hydraulic lines and the drive rod; and related investigative and corrective actions if PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 necessary. This proposed AD is prompted by a report of an aileron 2 fault caused by severe wear of the polyamide washer that is part of an antirotation bush assembly in the aileron attachment lug. We are proposing this AD to prevent excessive wear of the polyamide washer of the aileron actuator bush assembly, which could result in aileron flutter and loss of control of the airplane. DATES: We must receive comments on this proposed AD by May 6, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 20870; the directorate identifier for this docket is 2004–NM–180–AD. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20870; Directorate Identifier 2004–NM–180–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, E:\FR\FM\06APP1.SGM 06APP1 Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket website, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion The Civil Aviation Authority—The Netherlands (CAA–NL), which is the airworthiness authority for the Netherlands, notified us that an unsafe condition may exist on certain Fokker Model F.28 Mark 0070 and 0100 series airplanes. The CAA–NL advises that a Fokker Model F.28 0100 series airplane had an aileron 2 fault. Subsequent investigation showed severe wear of the polyamide washer that is used as part of an anti-rotation bush assembly in the aileron attachment lug. The worn washer allowed the aileron actuator to rotate inboard and caused the hydraulic unions at the actuator body to chafe through the drive rod of the aileron tab. This condition, if not corrected, could result in aileron flutter and loss of control of the airplane. Relevant Service Information Fokker Services B.V. has issued Fokker Service Bulletin SBF100–27– 083, dated October 20, 2003. The service bulletin describes procedures for a onetime inspection for chafing damage of VerDate jul<14>2003 15:58 Apr 05, 2005 Jkt 205001 the drive rod of the aileron tab. If the drive rod shows chafing damage, the service bulletin gives procedures for corrective actions. The corrective actions include reworking the drive rod to determine the depth of the chafing damage and the straightness of the drive rod; and replacing the drive rod with a new or serviceable rod if necessary: • For damage of less than or equal to .2 mm, no further action is required. • For damage of greater than .2 mm but less than .5 mm, replace the drive rod within 4,000 flight hours after the inspection. • For damage of greater than or equal to .5 mm but less than .8 mm, replace the drive rod within 500 flight hours after the inspection. • For damage of .8 mm or greater, replace the drive rod before further flight. The service bulletin also describes procedures for a one-time measurement for clearance between the aileron tab drive rod and the hydraulic lines of the aileron actuator. If the clearance is 4 mm or greater, the service bulletin states that no further action is required. If the clearance is less than 4 mm, the service bulletin gives procedures for one of two corrective actions: Replacing the polyamide washer with a new washer, or replacing the complete bush assembly with a new bush assembly. After the polyamide washer or bush assembly is replaced, the service bulletin gives procedures for the related investigative action of re-measuring the clearance between the aileron tab drive rod and the aileron actuator hydraulic line. If the measurement is 4 mm or greater, the service bulletin states that no further action is required. If the measurement is less than 4 mm, the corrective action is replacing the aileron actuator with a serviceable aileron at an applicable interval, depending on the clearance: • For clearance of 1 mm or less, replace the actuator before further flight. • For clearance more than 1 mm, but 2 mm or less, replace the actuator within 500 flight hours after the measurement. • For clearance of more than 2 mm to less than 4 mm, replace the actuator within 1,000 flight hours after the measurement. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The CAA–NL mandated the service information and issued Dutch airworthiness directive 2003–141, dated November 28, 2003, to ensure the continued airworthiness of these airplanes in the Netherlands. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 17343 FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in the Netherlands and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the CAA–NL has kept the FAA informed of the situation described above. We have examined the CAA–NL’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service bulletin described previously, except as discussed under ‘‘Difference Between the Proposed AD and the Dutch Airworthiness Directive.’’ Clarification of Inspection Type The service bulletin and the Dutch airworthiness directive do not specify the type of inspection to perform; we refer to the inspection as a ‘‘detailed’’ inspection. Note 1 of this proposed AD defines a detailed inspection. Difference Between the Proposed AD and the Dutch Airworthiness Directive The Dutch airworthiness directive does not include intervals for repeating the inspections of the drive rod assembly of the aileron tab, and the measurement of the clearance between the hydraulic line and the aileron tab drive rod. Instead, the Dutch airworthiness directive states that the repetitive intervals will be introduced separately in updates of the Fokker 70/ 100 Maintenance Review Board (MRB) document and the Aircraft Maintenance Manual (AMM). The CAA–NL requires operators in The Netherlands to use the information, including repetitive intervals, in the latest revision of the MRB and the AMM. However, since the MRB and AMM are not mandatory in the U.S., this proposed AD would mandate that operators repeat the inspections and measurement at intervals not to exceed 4,000 flight hours. We have determined that this repetitive interval would mandate the equivalent intervals specified in the MRB and AMM, and would address the unsafe condition in the same manner. This difference has been coordinated with the CAA–NL. E:\FR\FM\06APP1.SGM 06APP1 17344 Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Work hours Action Inspection ................................ Average labor rate per hour 1 $65 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate jul<14>2003 15:58 Apr 05, 2005 Jkt 205001 Cost per airplane Parts None .............................. No. of U.S.registered airplanes $65 2 Fleet cost $130, per inspection cycle. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Instructions of Fokker Service Bulletin SBF100–27–083, dated October 20, 2003. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (g) Within 24 months or 4,000 flight hours after the effective date of this AD, whichever occurs earlier: Do the actions in paragraphs (g)(1) and (g)(2) of this AD in accordance with the service bulletin. Repeat the actions thereafter at intervals not to exceed 4,000 flight hours. (1) Do a detailed inspection for chafing damage of the aileron tab drive rod assembly on each aileron actuator. (2) Measure the clearance between the hydraulic line and the aileron tab drive rod. 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 airworthiness directive (AD): Fokker Services B.V.: Docket No. FAA– 2005–20870; Directorate Identifier 2004– NM–180–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by May 6, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, certificated in any category. Unsafe Condition (d) This AD was prompted by a report of an aileron 2 fault caused by severe wear of the polyamide washer that is part of an antirotation bush assembly in the aileron attachment lug. We are issuing this AD to prevent excessive wear of the polyamide washer of the aileron actuator bush assembly, which could result in aileron flutter and loss of control of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Repetitive Inspections and Measurements Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Corrective Action for Chafing Damage (h) If any chafing damage that is greater than .2 mm is found during any inspection required by paragraph (g)(1) of this AD, replace the drive rod in accordance with the service bulletin, at the applicable threshold limits defined in the service bulletin. Corrective Action for Discrepant Clearance Measurements (i) If any clearance measurement that is outside the limits defined in the service bulletin is found during the action required by paragraph (g)(2) of this AD, do the actions in paragraphs (i)(1) and (i)(2) of this AD. Do all actions in accordance with the service bulletin at the applicable threshold limits defined in the service bulletin. (1) Replace the polyamide washer or replace the bush assembly. (2) Do all applicable related investigative and corrective actions after the replacement in paragraph (i)(1) of this AD, including replacing the aileron actuator with a serviceable aileron actuator as applicable. Alternative Methods of Compliance (AMOCs) (j) The Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, has the authority to approve AMOCs for this AD, if requested in E:\FR\FM\06APP1.SGM 06APP1 Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules accordance with the procedures found in 14 CFR 39.19. Related Information (k) Dutch airworthiness directive 2003– 141, dated November 28, 2003, also addresses the subject of this AD. Issued in Renton, Washington, on March 25, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6759 Filed 4–5–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20871; Directorate Identifier 2004–NM–212–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes. This proposed AD would require a detailed inspection to determine the presence of incorrectly installed bushings in the attachment holes of the reinforcing strap of the left- and right-hand wings’ lower skin, and corrective actions if necessary. This proposed AD is prompted by a report that bushings were installed in accordance with improper procedures in the structural repair manual. We are proposing this AD to detect and correct improperly installed bushings, which could result in reduced tensile strength of the reinforcing strap of the wing’s lower skin, and consequently a reduction of the structural capability of the wing and possible wing failure. DATES: We must receive comments on this proposed AD by May 6, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. VerDate jul<14>2003 19:40 Apr 05, 2005 Jkt 205001 • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 20871; the directorate identifier for this docket is 2004–NM–212–AD. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20871; Directorate Identifier 2004–NM–212–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 17345 Examining the Docket You can examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion The Civil Aviation Authority—The Netherlands (CAA–NL), which is the airworthiness authority for the Netherlands, notified us that an unsafe condition may exist on all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes. The CAA–NL advises that an operator found worn attachment holes in the reinforcing strap of a wing’s lower skin at wing station (WS) 2635. Subsequent investigation found that the repair bushings were improperly installed (with the bushings running completely through the wing skin and reinforcing strap) in a number of holes during the accomplishment of (optional) Fokker Service Bulletin F28/57–77. That service bulletin refers to the Structural Repair Manual (SRM) chapter 57–02–02, repair No. 3, for restoration of close tolerance holes by oversizing the holes or by installing bushings. The SRM has been updated and Fokker has issued Manual Change Notification— Maintenance F28–027 to correct the flawed SRM procedure. Although a joint with improperly installed bushings may still have adequate shear strength, its tensile strength is considerably reduced. For this reason, the applied repair is considered to be inadequate. Improperly installed bushings, if not detected and corrected, could result in reduced tensile strength of the reinforcing strap of the wing’s lower skin, and consequently a reduction of the structural capability of the wing and possible wing failure. Relevant Service Information Fokker Services B.V. has issued Fokker Service Bulletin F28/57–93, dated December 22, 2003. The service bulletin describes procedures for an inspection to determine the presence of incorrectly installed bushings in the attachment holes of the reinforcing strap of the left- and right-hand wings’ lower skin at WS 2635, and the repair of bushings, if necessary. E:\FR\FM\06APP1.SGM 06APP1

Agencies

[Federal Register Volume 70, Number 65 (Wednesday, April 6, 2005)]
[Proposed Rules]
[Pages 17342-17345]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6759]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20870; Directorate Identifier 2004-NM-180-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 
Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Fokker Model F.28 Mark 0070 and 0100 series airplanes. This 
proposed AD would require repetitive inspections for damage of the 
drive rod assembly of the aileron tab on each aileron actuator; 
repetitive measurements of the clearance between the aileron hydraulic 
lines and the drive rod; and related investigative and corrective 
actions if necessary. This proposed AD is prompted by a report of an 
aileron 2 fault caused by severe wear of the polyamide washer that is 
part of an anti-rotation bush assembly in the aileron attachment lug. 
We are proposing this AD to prevent excessive wear of the polyamide 
washer of the aileron actuator bush assembly, which could result in 
aileron flutter and loss of control of the airplane.

DATES: We must receive comments on this proposed AD by May 6, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the 
Netherlands.
    You can examine the contents of this AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-20870; the directorate identifier for this docket is 
2004-NM-180-AD.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20870; 
Directorate Identifier 2004-NM-180-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory,

[[Page 17343]]

economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket website, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit https://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    The Civil Aviation Authority--The Netherlands (CAA-NL), which is 
the airworthiness authority for the Netherlands, notified us that an 
unsafe condition may exist on certain Fokker Model F.28 Mark 0070 and 
0100 series airplanes. The CAA-NL advises that a Fokker Model F.28 0100 
series airplane had an aileron 2 fault. Subsequent investigation showed 
severe wear of the polyamide washer that is used as part of an anti-
rotation bush assembly in the aileron attachment lug. The worn washer 
allowed the aileron actuator to rotate inboard and caused the hydraulic 
unions at the actuator body to chafe through the drive rod of the 
aileron tab. This condition, if not corrected, could result in aileron 
flutter and loss of control of the airplane.

Relevant Service Information

    Fokker Services B.V. has issued Fokker Service Bulletin SBF100-27-
083, dated October 20, 2003. The service bulletin describes procedures 
for a one-time inspection for chafing damage of the drive rod of the 
aileron tab. If the drive rod shows chafing damage, the service 
bulletin gives procedures for corrective actions. The corrective 
actions include reworking the drive rod to determine the depth of the 
chafing damage and the straightness of the drive rod; and replacing the 
drive rod with a new or serviceable rod if necessary:
     For damage of less than or equal to .2 mm, no further 
action is required.
     For damage of greater than .2 mm but less than .5 mm, 
replace the drive rod within 4,000 flight hours after the inspection.
     For damage of greater than or equal to .5 mm but less than 
.8 mm, replace the drive rod within 500 flight hours after the 
inspection.
     For damage of .8 mm or greater, replace the drive rod 
before further flight.
    The service bulletin also describes procedures for a one-time 
measurement for clearance between the aileron tab drive rod and the 
hydraulic lines of the aileron actuator. If the clearance is 4 mm or 
greater, the service bulletin states that no further action is 
required. If the clearance is less than 4 mm, the service bulletin 
gives procedures for one of two corrective actions: Replacing the 
polyamide washer with a new washer, or replacing the complete bush 
assembly with a new bush assembly.
    After the polyamide washer or bush assembly is replaced, the 
service bulletin gives procedures for the related investigative action 
of re-measuring the clearance between the aileron tab drive rod and the 
aileron actuator hydraulic line. If the measurement is 4 mm or greater, 
the service bulletin states that no further action is required. If the 
measurement is less than 4 mm, the corrective action is replacing the 
aileron actuator with a serviceable aileron at an applicable interval, 
depending on the clearance:
     For clearance of 1 mm or less, replace the actuator before 
further flight.
     For clearance more than 1 mm, but 2 mm or less, replace 
the actuator within 500 flight hours after the measurement.
     For clearance of more than 2 mm to less than 4 mm, replace 
the actuator within 1,000 flight hours after the measurement.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The CAA-NL 
mandated the service information and issued Dutch airworthiness 
directive 2003-141, dated November 28, 2003, to ensure the continued 
airworthiness of these airplanes in the Netherlands.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in the Netherlands and are 
type certificated for operation in the United States under the 
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 
21.29) and the applicable bilateral airworthiness agreement. Pursuant 
to this bilateral airworthiness agreement, the CAA-NL has kept the FAA 
informed of the situation described above. We have examined the CAA-
NL's findings, evaluated all pertinent information, and determined that 
we need to issue an AD for products of this type design that are 
certificated for operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service bulletin described 
previously, except as discussed under ``Difference Between the Proposed 
AD and the Dutch Airworthiness Directive.''

Clarification of Inspection Type

    The service bulletin and the Dutch airworthiness directive do not 
specify the type of inspection to perform; we refer to the inspection 
as a ``detailed'' inspection. Note 1 of this proposed AD defines a 
detailed inspection.

Difference Between the Proposed AD and the Dutch Airworthiness 
Directive

    The Dutch airworthiness directive does not include intervals for 
repeating the inspections of the drive rod assembly of the aileron tab, 
and the measurement of the clearance between the hydraulic line and the 
aileron tab drive rod. Instead, the Dutch airworthiness directive 
states that the repetitive intervals will be introduced separately in 
updates of the Fokker 70/100 Maintenance Review Board (MRB) document 
and the Aircraft Maintenance Manual (AMM). The CAA-NL requires 
operators in The Netherlands to use the information, including 
repetitive intervals, in the latest revision of the MRB and the AMM. 
However, since the MRB and AMM are not mandatory in the U.S., this 
proposed AD would mandate that operators repeat the inspections and 
measurement at intervals not to exceed 4,000 flight hours. We have 
determined that this repetitive interval would mandate the equivalent 
intervals specified in the MRB and AMM, and would address the unsafe 
condition in the same manner.
    This difference has been coordinated with the CAA-NL.

[[Page 17344]]

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                         Average                                   No. of U.S.-
            Action              Work    labor rate        Parts         Cost per    registered     Fleet cost
                                hours    per hour                       airplane    airplanes
----------------------------------------------------------------------------------------------------------------
Inspection...................       1          $65  None............          $65            2  $130, per
                                                                                                 inspection
                                                                                                 cycle.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Fokker Services B.V.: Docket No. FAA-2005-20870; Directorate 
Identifier 2004-NM-180-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by May 6, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Fokker Model F.28 Mark 0070 and 0100 
series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD was prompted by a report of an aileron 2 fault 
caused by severe wear of the polyamide washer that is part of an 
anti-rotation bush assembly in the aileron attachment lug. We are 
issuing this AD to prevent excessive wear of the polyamide washer of 
the aileron actuator bush assembly, which could result in aileron 
flutter and loss of control of the airplane.

Compliance

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

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-27-
083, dated October 20, 2003.

Repetitive Inspections and Measurements

    (g) Within 24 months or 4,000 flight hours after the effective 
date of this AD, whichever occurs earlier: Do the actions in 
paragraphs (g)(1) and (g)(2) of this AD in accordance with the 
service bulletin. Repeat the actions thereafter at intervals not to 
exceed 4,000 flight hours.
    (1) Do a detailed inspection for chafing damage of the aileron 
tab drive rod assembly on each aileron actuator.
    (2) Measure the clearance between the hydraulic line and the 
aileron tab drive rod.


    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


Corrective Action for Chafing Damage

    (h) If any chafing damage that is greater than .2 mm is found 
during any inspection required by paragraph (g)(1) of this AD, 
replace the drive rod in accordance with the service bulletin, at 
the applicable threshold limits defined in the service bulletin.

Corrective Action for Discrepant Clearance Measurements

    (i) If any clearance measurement that is outside the limits 
defined in the service bulletin is found during the action required 
by paragraph (g)(2) of this AD, do the actions in paragraphs (i)(1) 
and (i)(2) of this AD. Do all actions in accordance with the service 
bulletin at the applicable threshold limits defined in the service 
bulletin.
    (1) Replace the polyamide washer or replace the bush assembly.
    (2) Do all applicable related investigative and corrective 
actions after the replacement in paragraph (i)(1) of this AD, 
including replacing the aileron actuator with a serviceable aileron 
actuator as applicable.

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate, has the authority to approve AMOCs for this 
AD, if requested in

[[Page 17345]]

accordance with the procedures found in 14 CFR 39.19.

Related Information

    (k) Dutch airworthiness directive 2003-141, dated November 28, 
2003, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 25, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-6759 Filed 4-5-05; 8:45 am]
BILLING CODE 4910-13-P
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