Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes, 78099-78101 [E6-22282]

Download as PDF Federal Register / Vol. 71, No. 249 / Thursday, December 28, 2006 / Proposed Rules Service Bulletin Exception (m) Although Bombardier Alert Service Bulletin A604–27–029, dated September 28, 2006, specifies to return certain parts to the manufacturer, this AD does not include that requirement. Reinsert AFM Revisions (n) For airplanes on which the AFM revisions required by paragraph (f) of this AD were removed from the applicable AFM before the effective date of this AD: Within 14 days after the effective date of this AD, reinsert the applicable AFM revisions specified in paragraph (f) of this AD. When the applicable TR specified in paragraph (f) of this AD has been included in the general revisions of the applicable AFM, the applicable TR may be removed. Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, New York Aircraft Certification Office, FAA, 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 (p) Canadian airworthiness directives CF– 2006–20R1, dated October 4, 2006, and CF– 2006–21R1, dated October 3, 2006, also address the subject of this AD. Issued in Renton, Washington, on December 14, 2006. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–22271 Filed 12–27–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26709; Directorate Identifier 2006–NM–202–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes 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 inspecting the carbon-fiber VerDate Aug<31>2005 15:22 Dec 27, 2006 Jkt 211001 reinforced plastic (CFRP) main landing gear (MLG) door to determine whether certain part numbers are installed. For airplanes having certain doors, this proposed AD would require inspecting the MLG outboard door for cracks, play, and loose sealant/bolts/nuts, and related investigative and corrective actions if necessary. This proposed AD would also require, for airplanes having certain doors, modifying the rod bracket attachment of the MLG outboard door. This proposed AD results from a report of a rod bracket of the MLG door detaching during flight. We are proposing this AD to detect and correct cracks in the rod bracket attachment bolts, which could result in the rod brackets detaching from the MLG door and blocking the proper functioning of the MLG. DATES: We must receive comments on this proposed AD by January 29, 2007. 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. • 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, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; 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–2006–26709; Directorate Identifier 2006–NM–202–AD’’ at the beginning of your comments. We specifically invite comments on the PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 78099 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 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 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 https:// dms.dot.gov. Examining the Docket You may 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 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 Fokker Model F.28 Mark 0070 and 0100 airplanes equipped with certain carbon-fiber reinforced plastic (CFRP) main landing gear (MLG) doors. The CAA–NL reports that a rod bracket of the MLG door of a Model F.28 Mark 0070 airplane detached during flight. Investigation showed that the operating rod between the MLG outboard door and the MLG fitting was broken and the rod’s bracket was detached from the outboard door. The affected parts subsequently got stuck between the MLG and the outboard door hinge, resulting in damage to the two adjacent hydraulic lines. An investigation of a similar event revealed an operating rod bracket broken loose from the CFRP MLG door. Several other operators have also reported finding partly detached operating rod brackets. This condition, if not corrected, could result in rod E:\FR\FM\28DEP1.SGM 28DEP1 78100 Federal Register / Vol. 71, No. 249 / Thursday, December 28, 2006 / Proposed Rules brackets detaching from the CFRP MLG outboard door and blocking the proper functioning of the MLG. Relevant Service Information Fokker Services B.V. has issued Fokker Service Bulletin SBF100–52– 080, dated December 12, 2005, including Fokker Manual Change Notification—Maintenance Documentation MCNM–F100–103, dated November 15, 2005. In Part 1 of the Accomplishment Instructions of the service bulletin, the service bulletin describes procedures for doing a detailed inspection of the MLG outboard door for cracks, play, and loose sealant/bolts/nuts. The detailed inspection consists of the following actions: • Inspecting for any cracks in the CFRP skin of the MLG outboard door. • Inspecting for play between the countersunk bolt-heads and the CFRP outer skin. • Inspecting for cracks in the paint. • Inspecting for play between the operating rod bracket and the MLG outboard door. • Inspecting for loose sealant around the edges of the bracket and loose bolts and nuts. Part 1 of the service bulletin also describes doing the following related investigative action if play is found or if there are any loose bolts/nuts: Inspecting the inside of the door for cracks in the CFRP outer skin at the bolt hole locations and/or checking for delamination by tapping. Part 1 of the service bulletin also describes doing one of the following corrective actions if play is found, if there are any loose bolts/nuts, or if any crack is found: Contacting Fokker, operating under Configuration Deviation List (CDL) item 52–07 (‘‘operating with MLG strut bay doors missing’’) of the Fokker Appendix CDL, to Fokker 70/ Fokker 100 Airplane Flight Manual (AFM), Version 06, Issue 010, or doing the modification of the MLG outboard door operating rod bracket attachment specified in Part 2 of the service bulletin. Part 2 of the Accomplishment Instructions of the service bulletin describes procedures for modifying the MLG outboard door operating rod bracket attachment. The modification includes installing internal and external reinforcement plates, reidentifying the outboard MLG door, and doing the following related investigative actions and corrective actions: • Inspecting for damage of the operating rod bracket and operating rod. • If any damage is found, doing one of the following: contacting Fokker, operating under CDL item 52–07, or replacing damaged part with a new part. • Inspecting for cracks and and/or checking for delamination by tapping of the skin around the attachment holes. • If any crack or delamination is found, doing one of the following: Repairing the cracks or delamination, or contacting Fokker if any crack or delamination is found beyond 10 millimeters (mm) (0.040 inches) from the bolt holes. 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 NL–2006–001, dated January 5, 2006, 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 Between the Proposed AD and the Service Bulletin.’’ Difference Between the Proposed AD 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. Clarification of Service Bulletin Paragraph B.(3) of Part 1 of the Accomplishment Instructions of the service bulletin specifies to inspect for loose sealant and paragraph B.(6) specifies to inspect for delamination. However corrective actions for those conditions are not specified in the service bulletin. This proposed AD would require doing the corrective action specified in paragraph C.(3) of the service bulletin if any loose sealant or delamination is found during any inspection specified in paragraph (g) of the proposed AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS cprice-sewell on PROD1PC66 with PROPOSALS Action Work hours Inspections ....................................................................... Modification ...................................................................... Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Aug<31>2005 15:22 Dec 27, 2006 Jkt 211001 2 6 Average labor rate per hour $80 80 Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Cost per airplane Parts $0 1,066 $160 1,546 Number of U.S.registered airplanes 7 7 Fleet cost $1,120 10,822 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 E:\FR\FM\28DEP1.SGM 28DEP1 Federal Register / Vol. 71, No. 249 / Thursday, December 28, 2006 / Proposed Rules 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: 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. cprice-sewell on PROD1PC66 with PROPOSALS § 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– 26709; Directorate Identifier 2006–NM– 202–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 29, 2007. VerDate Aug<31>2005 15:22 Dec 27, 2006 Jkt 211001 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 a report of a rod bracket of the main landing gear (MLG) door detaching during flight. We are issuing this AD to detect and correct cracks in the rod bracket attachment bolts, which could result in the rod brackets detaching from the MLG door and blocking the proper functioning of the MLG. 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. Inspections (f) Within nine months after the effective date of this AD, inspect the carbon-fiber reinforced plastic (CFRP) MLG doors to determine if any MLG door having a part number (P/N) D13312–401 through –410 inclusive is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the CFRP MLG doors can be conclusively determined from that review. If the CFRP MLG doors have any part number other than P/N D13312–401 through –410 inclusive installed, no further action is required by this AD. (g) If any CFRP MLG door having any P/N D13312–401 through–410 inclusive is found during the inspection required by paragraph (f) of this AD: Within nine months after the effective date of this AD, do a detailed inspection of the MLG outboard door for cracks, play, and loose sealant/bolts/ nuts as specified in Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–52–080, dated December 12, 2005, including Fokker Manual Change Notification—Maintenance Documentation MCNM–F100–103, dated November 15, 2005, and do all applicable related investigative and corrective actions, by doing all the applicable actions specified in Part 1 of the Accomplishment Instructions of the service bulletin, except as provided by paragraphs (i), (j), and (k) of this AD. Do all applicable related investigative and corrective actions before further flight. 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.’’ Modification (h) If any CFRP MLG door having any P/N D13312–401 through–410 inclusive is found during the inspection required by PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 78101 paragraph (f) of this AD: Within 12 months after the effective date of this AD, modify the MLG outboard door operating rod bracket attachment and do all applicable related investigative and corrective actions by doing all the applicable actions specified in Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–52–080, dated December 12, 2005, including Fokker Manual Change Notification—Maintenance Documentation MCNM–F100–103, dated November 15, 2005, except as provided by paragraph (i) of this AD. Do all applicable related investigative and corrective actions before further flight. Exceptions to the Service Bulletin (i) Where Fokker Service Bulletin SBF100– 52–080, dated December 12, 2005, including Fokker Manual Change Notification— Maintenance Documentation MCNM–F100– 103, dated November 15, 2005, specifies to contact the manufacturer for repair, before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). (j) If any loose sealant or any delamination is found during any inspection required by paragraph (g) of this AD, before further flight, do the corrective action specified in paragraph C.(3) of Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–52–080, dated December 12, 2005, including Fokker Manual Change Notification—Maintenance Documentation MCNM–F100–103, dated November 15, 2005. (k) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (l)(1) 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. (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 (m) Dutch airworthiness directive NL– 2006–001, dated January 5, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on December 19, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–22282 Filed 12–27–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\28DEP1.SGM 28DEP1

Agencies

[Federal Register Volume 71, Number 249 (Thursday, December 28, 2006)]
[Proposed Rules]
[Pages 78099-78101]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-22282]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26709; Directorate Identifier 2006-NM-202-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 inspecting the carbon-fiber reinforced plastic (CFRP) 
main landing gear (MLG) door to determine whether certain part numbers 
are installed. For airplanes having certain doors, this proposed AD 
would require inspecting the MLG outboard door for cracks, play, and 
loose sealant/bolts/nuts, and related investigative and corrective 
actions if necessary. This proposed AD would also require, for 
airplanes having certain doors, modifying the rod bracket attachment of 
the MLG outboard door. This proposed AD results from a report of a rod 
bracket of the MLG door detaching during flight. We are proposing this 
AD to detect and correct cracks in the rod bracket attachment bolts, 
which could result in the rod brackets detaching from the MLG door and 
blocking the proper functioning of the MLG.

DATES: We must receive comments on this proposed AD by January 29, 
2007.

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.
     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, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; 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-
26709; Directorate Identifier 2006-NM-202-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 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 
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 https://dms.dot.gov.

Examining the Docket

    You may 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 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 Fokker Model F.28 Mark 0070 and 0100 
airplanes equipped with certain carbon-fiber reinforced plastic (CFRP) 
main landing gear (MLG) doors. The CAA-NL reports that a rod bracket of 
the MLG door of a Model F.28 Mark 0070 airplane detached during flight. 
Investigation showed that the operating rod between the MLG outboard 
door and the MLG fitting was broken and the rod's bracket was detached 
from the outboard door. The affected parts subsequently got stuck 
between the MLG and the outboard door hinge, resulting in damage to the 
two adjacent hydraulic lines. An investigation of a similar event 
revealed an operating rod bracket broken loose from the CFRP MLG door. 
Several other operators have also reported finding partly detached 
operating rod brackets. This condition, if not corrected, could result 
in rod

[[Page 78100]]

brackets detaching from the CFRP MLG outboard door and blocking the 
proper functioning of the MLG.

Relevant Service Information

    Fokker Services B.V. has issued Fokker Service Bulletin SBF100-52-
080, dated December 12, 2005, including Fokker Manual Change 
Notification--Maintenance Documentation MCNM-F100-103, dated November 
15, 2005.
    In Part 1 of the Accomplishment Instructions of the service 
bulletin, the service bulletin describes procedures for doing a 
detailed inspection of the MLG outboard door for cracks, play, and 
loose sealant/bolts/nuts. The detailed inspection consists of the 
following actions:
     Inspecting for any cracks in the CFRP skin of the MLG 
outboard door.
     Inspecting for play between the countersunk bolt-heads and 
the CFRP outer skin.
     Inspecting for cracks in the paint.
     Inspecting for play between the operating rod bracket and 
the MLG outboard door.
     Inspecting for loose sealant around the edges of the 
bracket and loose bolts and nuts.
    Part 1 of the service bulletin also describes doing the following 
related investigative action if play is found or if there are any loose 
bolts/nuts: Inspecting the inside of the door for cracks in the CFRP 
outer skin at the bolt hole locations and/or checking for delamination 
by tapping.
    Part 1 of the service bulletin also describes doing one of the 
following corrective actions if play is found, if there are any loose 
bolts/nuts, or if any crack is found: Contacting Fokker, operating 
under Configuration Deviation List (CDL) item 52-07 (``operating with 
MLG strut bay doors missing'') of the Fokker Appendix CDL, to Fokker 
70/Fokker 100 Airplane Flight Manual (AFM), Version 06, Issue 010, or 
doing the modification of the MLG outboard door operating rod bracket 
attachment specified in Part 2 of the service bulletin.
    Part 2 of the Accomplishment Instructions of the service bulletin 
describes procedures for modifying the MLG outboard door operating rod 
bracket attachment. The modification includes installing internal and 
external reinforcement plates, reidentifying the outboard MLG door, and 
doing the following related investigative actions and corrective 
actions:
     Inspecting for damage of the operating rod bracket and 
operating rod.
     If any damage is found, doing one of the following: 
contacting Fokker, operating under CDL item 52-07, or replacing damaged 
part with a new part.
     Inspecting for cracks and and/or checking for delamination 
by tapping of the skin around the attachment holes.
     If any crack or delamination is found, doing one of the 
following: Repairing the cracks or delamination, or contacting Fokker 
if any crack or delamination is found beyond 10 millimeters (mm) (0.040 
inches) from the bolt holes.
    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 NL-2006-001, dated January 5, 2006, 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 Between 
the Proposed AD and the Service Bulletin.''

Difference Between the Proposed AD 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.

Clarification of Service Bulletin

    Paragraph B.(3) of Part 1 of the Accomplishment Instructions of the 
service bulletin specifies to inspect for loose sealant and paragraph 
B.(6) specifies to inspect for delamination. However corrective actions 
for those conditions are not specified in the service bulletin. This 
proposed AD would require doing the corrective action specified in 
paragraph C.(3) of the service bulletin if any loose sealant or 
delamination is found during any inspection specified in paragraph (g) 
of the proposed AD.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number of
                                                   Average                   Cost per      U.S.-
              Action                 Work hours   labor rate     Parts       airplane    registered   Fleet cost
                                                   per hour                              airplanes
----------------------------------------------------------------------------------------------------------------
Inspections.......................            2          $80           $0         $160            7       $1,120
Modification......................            6           80        1,066        1,546            7       10,822
----------------------------------------------------------------------------------------------------------------

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

[[Page 78101]]

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:

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-2006-26709; Directorate 
Identifier 2006-NM-202-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
29, 2007.

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 a report of a rod bracket of the main 
landing gear (MLG) door detaching during flight. We are issuing this 
AD to detect and correct cracks in the rod bracket attachment bolts, 
which could result in the rod brackets detaching from the MLG door 
and blocking the proper functioning of the MLG.

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.

Inspections

    (f) Within nine months after the effective date of this AD, 
inspect the carbon-fiber reinforced plastic (CFRP) MLG doors to 
determine if any MLG door having a part number (P/N) D13312-401 
through -410 inclusive is installed. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part number of the CFRP MLG doors can be conclusively determined 
from that review. If the CFRP MLG doors have any part number other 
than P/N D13312-401 through -410 inclusive installed, no further 
action is required by this AD.
    (g) If any CFRP MLG door having any P/N D13312-401 through-410 
inclusive is found during the inspection required by paragraph (f) 
of this AD: Within nine months after the effective date of this AD, 
do a detailed inspection of the MLG outboard door for cracks, play, 
and loose sealant/bolts/nuts as specified in Part 1 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-52-
080, dated December 12, 2005, including Fokker Manual Change 
Notification--Maintenance Documentation MCNM-F100-103, dated 
November 15, 2005, and do all applicable related investigative and 
corrective actions, by doing all the applicable actions specified in 
Part 1 of the Accomplishment Instructions of the service bulletin, 
except as provided by paragraphs (i), (j), and (k) of this AD. Do 
all applicable related investigative and corrective actions before 
further flight.

    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.''

Modification

    (h) If any CFRP MLG door having any P/N D13312-401 through-410 
inclusive is found during the inspection required by paragraph (f) 
of this AD: Within 12 months after the effective date of this AD, 
modify the MLG outboard door operating rod bracket attachment and do 
all applicable related investigative and corrective actions by doing 
all the applicable actions specified in Part 2 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-52-080, dated 
December 12, 2005, including Fokker Manual Change Notification--
Maintenance Documentation MCNM-F100-103, dated November 15, 2005, 
except as provided by paragraph (i) of this AD. Do all applicable 
related investigative and corrective actions before further flight.

Exceptions to the Service Bulletin

    (i) Where Fokker Service Bulletin SBF100-52-080, dated December 
12, 2005, including Fokker Manual Change Notification--Maintenance 
Documentation MCNM-F100-103, dated November 15, 2005, specifies to 
contact the manufacturer for repair, before further flight, repair 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent).
    (j) If any loose sealant or any delamination is found during any 
inspection required by paragraph (g) of this AD, before further 
flight, do the corrective action specified in paragraph C.(3) of 
Part 1 of the Accomplishment Instructions of Fokker Service Bulletin 
SBF100-52-080, dated December 12, 2005, including Fokker Manual 
Change Notification--Maintenance Documentation MCNM-F100-103, dated 
November 15, 2005.
    (k) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (l)(1) 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.
    (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

    (m) Dutch airworthiness directive NL-2006-001, dated January 5, 
2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on December 19, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-22282 Filed 12-27-06; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.