Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes, 33260-33262 [E6-8897]

Download as PDF 33260 Proposed Rules Federal Register Vol. 71, No. 110 Thursday, June 8, 2006 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24959; Directorate Identifier 2005–NM–258–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes Comments Invited Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). cprice-sewell on PROD1PC66 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This proposed AD would require a one-time detailed inspection to detect corrosion on the wing rear spar lower girder, and related investigative and applicable corrective actions if necessary. This proposed AD results from reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200. We are proposing this AD to detect and correct corrosion of the wing rear spar lower girder, which could result in reduced structural integrity of the wing rear spar. DATES: We must receive comments on this proposed AD by July 10, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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. • Fax: (202) 493–2251. VerDate Aug<31>2005 15:22 Jun 07, 2006 Jkt 208001 • 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. Contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98055–4056; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–24959; Directorate Identifier 2005–NM–258–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 received 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 http:// 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 that 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 may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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 Docket Management System 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 0070 and 0100 airplanes. The CAA–NL advises that it has received reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200 on several Fokker Model F.28 Mark 0100 airplanes. The exfoliation corrosion was found when the aileron pulley assembly was removed from the airplane. In at least one case, replacement of a section of the rear spar lower girder was necessary to return the airplane back to service. This particular part of the wing is visible only through a narrow slot between the aileron pulley assembly and the rear spar, and through small lightening holes in the aileron pulley attachment bracket. Therefore, it is possible that any corrosion in this area could remain undetected during routine inspections of fuselage zones 536 and 636 done in accordance with Tasks 062505–00–01 and 062605–00–01 of the Fokker 70/100 Maintenance Review Board Document. The cause of the corrosion is unknown. Corrosion of the wing rear spar lower girder, if not corrected, could result in corrosion remaining undetected, resulting in reduced structural integrity of the wing rear spar. The design of the wing rear spar lower girder on Fokker Model F.28 Mark 0070 airplanes is the same as on Model F.28 Mark 0100 airplanes; therefore, the unsafe condition could exist on all of these airplanes. Relevant Service Information Fokker Services B.V. has issued Service Bulletin SBF100–57–038, dated April 15, 2005. The service bulletin describes procedures for doing a onetime detailed inspection of the wing rear spar lower girder between STA 8700 and STA 9200 for corrosion, and related investigative and applicable corrective actions if necessary. If corrosion is found, the related investigative actions E:\FR\FM\08JNP1.SGM 08JNP1 33261 Federal Register / Vol. 71, No. 110 / Thursday, June 8, 2006 / Proposed Rules include removing the aileron pulley assembly, removing the corrosion from the wing rear spar lower girder, and measuring the depth of the damaged spots. The corrective actions include repairing the wing rear spar lower girder if the damage is outside of specified limits and repairing the surface treatment. The service bulletin also describes procedures for reporting inspection and damage findings to the manufacturer. The CAA–NL mandated the service information and issued Dutch airworthiness directive NL–2005– 006, dated April 29, 2005, 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 airplanes 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 information described previously, except as discussed under ‘‘Differences Among the Proposed AD, the Dutch Airworthiness Directive, and the Service Bulletin.’’ The proposed AD would also require sending the inspection results to the FAA. have determined that, for this proposed AD, any damage found that measures more than or equal to 1.3 mm deep or when the remaining material of the rear spar lower girder is less than or equal to 2.1 mm thick, must be repaired in accordance with a method approved by us; or the EASA (or its delegated agent). Differences Among the Proposed AD, the Dutch Airworthiness Directive, and the Service Bulletin The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions using a method that we or the European Aviation Safety Agency (EASA) (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the EASA approve would be acceptable for compliance with this proposed AD. The service bulletin specifies procedures to take when the damage is more than 1.3 millimeters (mm) deep and when the remaining material of the rear spar lower girder is less than 2.1 mm thick, but it does not specify what to do if the depth is exactly 1.3 mm and the thickness is exactly 2.1 mm. We The Dutch airworthiness directive refers only to an ‘‘inspection’’ for corrosion of the wing rear spar lower girder. We have determined that the procedures in the service bulletin should be described—as they are in the service bulletin—as a ‘‘detailed inspection.’’ We have included Note 1 in this proposed AD to define this type of inspection. Clarification of Inspection Type Interim Action This proposed AD is considered to be interim action. The inspection reports that would be required by this proposed AD would enable the manufacturer to obtain better insight into the nature, cause, and extent of the corrosion, and eventually to develop final action to address the unsafe condition. Once final action has been identified, we may consider further rulemaking. 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 of wing rear spar lower girder ........................ cprice-sewell on PROD1PC66 with PROPOSALS 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 VerDate Aug<31>2005 14:58 Jun 07, 2006 Jkt 208001 Average labor rate per hour 2 $80 Parts $0 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Cost per airplane $160 Number of U.S.-registered airplanes Fleet cost 44 $7,040 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 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, 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: E:\FR\FM\08JNP1.SGM 08JNP1 33262 Federal Register / Vol. 71, No. 110 / Thursday, June 8, 2006 / Proposed Rules 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.’’ 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Fokker Services B.V.: Docket No. FAA– 2006–24959; Directorate Identifier 2005– NM–258–AD. Comments Due Date (a) The FAA must receive comments on this AD action by July 10, 2006. Affected ADs (b) None. Applicability (c) This AD applies to all Fokker Model F.28 Mark 0070 and 0100 airplanes, certificated in any category. Unsafe Condition (d) This AD results from reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200. We are issuing this AD to detect and correct corrosion of the wing rear spar lower girder, which, if not detected, could result in reduced structural integrity of the wing rear spar. cprice-sewell on PROD1PC66 with PROPOSALS 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. Wing Rear Spar Lower Girder Inspection/ Related Investigative/Corrective Actions (f) Within 4,000 flight hours or 21 months after the effective date of this AD, whichever occurs first: Do a detailed inspection to detect corrosion on the wing rear spar lower girder between wing STA 8700 and wing STA 9200, and do all related investigative and applicable corrective actions by accomplishing all the actions specified in the Accomplishment Instructions of Fokker Service Bulletin SBF100–57–038, dated April 15, 2005, except as provided by paragraphs (g) and (h) of this AD. Do all related investigative and corrective actions before further flight. If any damage found that measures more than or equal to 1.3 millimeters (mm) deep, or if the thickness of the remaining material of the rear spar lower girder is less than or equal to 2.1 mm thick, repair in accordance with a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). 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 VerDate Aug<31>2005 14:58 Jun 07, 2006 Jkt 208001 DEPARTMENT OF TRANSPORTATION (g) If, during the accomplishment of the corrective actions required by paragraph (f) of this AD, the service bulletin specifies contacting the manufacturer for certain repair instructions: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). [Docket No. FAA–2006–24978; Directorate Identifier 2006–NM–108–AD] Reporting Inspection and Damage Results (h) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f) of this AD to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; fax +31 252 627211; e-mail Technicalservices.FokkerServices@stork.com; at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. Use the reporting forms in Figures 3 and 4 of Fokker Service Bulletin SBF100–57–038, dated April 15, 2005. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (j) Dutch airworthiness directive NL–2005– 006, dated April 29, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on May 30, 2006. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–8897 Filed 6–7–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model 717–200 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 certain McDonnell Douglas Model 717– 200 airplanes. This proposed AD would require modifying the fuel boost pump container of the center tank. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent exposing the fuel pump container vapor area to electrical arcing during a fuel pump motor case or connector burn through, which could result in a fuel tank explosion. DATES: We must receive comments on this proposed AD by July 24, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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. • 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. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: William Bond, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; E:\FR\FM\08JNP1.SGM 08JNP1

Agencies

[Federal Register Volume 71, Number 110 (Thursday, June 8, 2006)]
[Proposed Rules]
[Pages 33260-33262]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-8897]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 71, No. 110 / Thursday, June 8, 2006 / 
Proposed Rules

[[Page 33260]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24959; Directorate Identifier 2005-NM-258-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 
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 airplanes. This proposed 
AD would require a one-time detailed inspection to detect corrosion on 
the wing rear spar lower girder, and related investigative and 
applicable corrective actions if necessary. This proposed AD results 
from reports of corrosion of the wing rear spar lower girder between 
wing station (STA) 8700 and wing STA 9200. We are proposing this AD to 
detect and correct corrosion of the wing rear spar lower girder, which 
could result in reduced structural integrity of the wing rear spar.

DATES: We must receive comments on this proposed AD by July 10, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
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.
     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.
    Contact Fokker Services B.V., Technical Services Dept., P.O. Box 
231, 2150 AE Nieuw-Vennep, the Netherlands, for service information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 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 in the ADDRESSES section. Include the docket number ``FAA-2006-
24959; Directorate Identifier 2005-NM-258-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 received 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 http://
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 
that 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 may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://
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 Docket Management System 
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 0070 and 0100 
airplanes. The CAA-NL advises that it has received reports of corrosion 
of the wing rear spar lower girder between wing station (STA) 8700 and 
wing STA 9200 on several Fokker Model F.28 Mark 0100 airplanes. The 
exfoliation corrosion was found when the aileron pulley assembly was 
removed from the airplane. In at least one case, replacement of a 
section of the rear spar lower girder was necessary to return the 
airplane back to service. This particular part of the wing is visible 
only through a narrow slot between the aileron pulley assembly and the 
rear spar, and through small lightening holes in the aileron pulley 
attachment bracket. Therefore, it is possible that any corrosion in 
this area could remain undetected during routine inspections of 
fuselage zones 536 and 636 done in accordance with Tasks 062505-00-01 
and 062605-00-01 of the Fokker 70/100 Maintenance Review Board 
Document. The cause of the corrosion is unknown. Corrosion of the wing 
rear spar lower girder, if not corrected, could result in corrosion 
remaining undetected, resulting in reduced structural integrity of the 
wing rear spar.
    The design of the wing rear spar lower girder on Fokker Model F.28 
Mark 0070 airplanes is the same as on Model F.28 Mark 0100 airplanes; 
therefore, the unsafe condition could exist on all of these airplanes.

Relevant Service Information

    Fokker Services B.V. has issued Service Bulletin SBF100-57-038, 
dated April 15, 2005. The service bulletin describes procedures for 
doing a one-time detailed inspection of the wing rear spar lower girder 
between STA 8700 and STA 9200 for corrosion, and related investigative 
and applicable corrective actions if necessary. If corrosion is found, 
the related investigative actions

[[Page 33261]]

include removing the aileron pulley assembly, removing the corrosion 
from the wing rear spar lower girder, and measuring the depth of the 
damaged spots. The corrective actions include repairing the wing rear 
spar lower girder if the damage is outside of specified limits and 
repairing the surface treatment. The service bulletin also describes 
procedures for reporting inspection and damage findings to the 
manufacturer. The CAA-NL mandated the service information and issued 
Dutch airworthiness directive NL-2005-006, dated April 29, 2005, 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 airplanes 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 information 
described previously, except as discussed under ``Differences Among the 
Proposed AD, the Dutch Airworthiness Directive, and the Service 
Bulletin.'' The proposed AD would also require sending the inspection 
results to the FAA.

Differences Among the Proposed AD, the Dutch Airworthiness Directive, 
and the Service Bulletin

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions using a method that we or the 
European Aviation Safety Agency (EASA) (or its delegated agent) 
approve. In light of the type of repair that would be required to 
address the unsafe condition, and consistent with existing bilateral 
airworthiness agreements, we have determined that, for this proposed 
AD, a repair we or the EASA approve would be acceptable for compliance 
with this proposed AD.
    The service bulletin specifies procedures to take when the damage 
is more than 1.3 millimeters (mm) deep and when the remaining material 
of the rear spar lower girder is less than 2.1 mm thick, but it does 
not specify what to do if the depth is exactly 1.3 mm and the thickness 
is exactly 2.1 mm. We have determined that, for this proposed AD, any 
damage found that measures more than or equal to 1.3 mm deep or when 
the remaining material of the rear spar lower girder is less than or 
equal to 2.1 mm thick, must be repaired in accordance with a method 
approved by us; or the EASA (or its delegated agent).

Clarification of Inspection Type

    The Dutch airworthiness directive refers only to an ``inspection'' 
for corrosion of the wing rear spar lower girder. We have determined 
that the procedures in the service bulletin should be described--as 
they are in the service bulletin--as a ``detailed inspection.'' We have 
included Note 1 in this proposed AD to define this type of inspection.

Interim Action

    This proposed AD is considered to be interim action. The inspection 
reports that would be required by this proposed AD would enable the 
manufacturer to obtain better insight into the nature, cause, and 
extent of the corrosion, and eventually to develop final action to 
address the unsafe condition. Once final action has been identified, we 
may consider further rulemaking.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
            Action                Work    Average labor   Parts      Cost per       registered      Fleet cost
                                 hours    rate per hour              airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Inspection of wing rear spar          2             $80       $0            $160              44          $7,040
 lower girder.................
----------------------------------------------------------------------------------------------------------------

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 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, 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:

[[Page 33262]]

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Fokker Services B.V.: Docket No. FAA-2006-24959; Directorate 
Identifier 2005-NM-258-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 10, 
2006.

Affected ADs

    (b) None.

Applicability

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

Unsafe Condition

    (d) This AD results from reports of corrosion of the wing rear 
spar lower girder between wing station (STA) 8700 and wing STA 9200. 
We are issuing this AD to detect and correct corrosion of the wing 
rear spar lower girder, which, if not detected, could result in 
reduced structural integrity of the wing rear spar.

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.

Wing Rear Spar Lower Girder Inspection/Related Investigative/Corrective 
Actions

    (f) Within 4,000 flight hours or 21 months after the effective 
date of this AD, whichever occurs first: Do a detailed inspection to 
detect corrosion on the wing rear spar lower girder between wing STA 
8700 and wing STA 9200, and do all related investigative and 
applicable corrective actions by accomplishing all the actions 
specified in the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-57-038, dated April 15, 2005, except as provided by 
paragraphs (g) and (h) of this AD. Do all related investigative and 
corrective actions before further flight. If any damage found that 
measures more than or equal to 1.3 millimeters (mm) deep, or if the 
thickness of the remaining material of the rear spar lower girder is 
less than or equal to 2.1 mm thick, repair in accordance with a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA) (or its delegated agent).

    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.''


    (g) If, during the accomplishment of the corrective actions 
required by paragraph (f) of this AD, the service bulletin specifies 
contacting the manufacturer for certain repair instructions: Before 
further flight, repair in accordance with a method approved by the 
Manager, International Branch, ANM-116; or the EASA (or its 
delegated agent).

Reporting Inspection and Damage Results

    (h) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (f) of this AD to Fokker 
Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE 
Nieuw-Vennep, the Netherlands; fax +31 252 627211; e-mail 
Technicalservices.FokkerServices@stork.com; at the applicable time 
specified in paragraph (h)(1) or (h)(2) of this AD. Use the 
reporting forms in Figures 3 and 4 of Fokker Service Bulletin 
SBF100-57-038, dated April 15, 2005. Under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office 
of Management and Budget (OMB) has approved the information 
collection requirements contained in this AD and has assigned OMB 
Control Number 2120-0056.
    (1) If the inspection was done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (j) Dutch airworthiness directive NL-2005-006, dated April 29, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on May 30, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-8897 Filed 6-7-06; 8:45 am]
BILLING CODE 4910-13-P