[Federal Register Volume 72, Number 47 (Monday, March 12, 2007)]
[Proposed Rules]
[Pages 10951-10953]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-4379]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27509; Directorate Identifier 2006-NM-201-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).

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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 detailed inspection for wear of the attachment holes 
of the control levers of the braking system and applicable corrective 
actions. This proposed AD results from a report that, after landing, 
the flightcrew of a Model F.28 Mark 0100 airplane noted that an extreme 
difference in pedal angle was required to achieve equal braking action. 
We are proposing this AD to prevent failure of one or more brake 
control levers, which could result in uncommanded braking and loss of 
control of the airplane during takeoff, landing, or taxiing.

DATES: We must receive comments on this proposed AD by April 11, 2007.

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, 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-2007-
27509; Directorate Identifier 2006-NM-201-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

[[Page 10952]]

condition may exist on all Fokker Model F.28 Mark 0070 and 0100 
airplanes. The CAA-NL advises of a report that, after landing, the 
flightcrew of a Model F.28 Mark 0100 airplane noted that an extreme 
difference in pedal angle was required to achieve equal braking action; 
concurrently, the temperature of the left-hand braking system was noted 
to be considerably higher than the right-hand braking system. 
Investigation revealed that the attachment holes of the control levers 
of the braking system were worn to the point of imminent failure. The 
airplane and affected levers had accumulated 15,583 total flight cycles 
and 21,460 total flight hours. This condition, if not corrected, could 
lead to failure of one or more brake levers, which could result in 
uncommanded braking and loss of control of the airplane during take-
off, landing, or taxiing.

Relevant Service Information

    Fokker Services B.V. has issued Fokker Service Bulletin SBF100-32-
142, dated August 12, 2005. The service bulletin describes procedures 
for inspecting for wear of the attachment holes of the control levers 
of the braking system and applicable corrective actions. Corrective 
actions include replacing the control levers with new control levers at 
times determined by the level of wear found during the inspection. 
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-2005-011, dated August 31, 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 
Information.''

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

    The Fokker service bulletin and the Dutch airworthiness directive 
describe a one-time inspection for wear of the attachment holes of the 
control levers. However, we have determined that confusion might occur 
regarding the inspection of any replacement control levers. Therefore, 
this proposed AD would require inspecting any replacement control lever 
for wear of the attachment holes, at an interval not to exceed 12,000 
flight hours after the installation of any such lever, and applicable 
corrective actions thereafter, as described by the service information.
    The service bulletin refers to a ``detailed visual inspection'' for 
wear of the attachment holes of the control levers. We have determined 
that the procedures in the service bulletin should be described as a 
``detailed inspection.'' We have included a definition of this type of 
inspection in Note 1 of this proposed AD.
    Where the service bulletin specifies immediate replacement of the 
control lever if the applicable remaining material (dimension X2) of 
the attachment hole is less than 2.0 millimeters (0.08 inches), this 
proposed AD would direct operators to replace the control lever if 
dimension X2 is less than or equal to 2.0 millimeters.
    These differences have been coordinated with the CAA-NL.

Costs of Compliance

    This proposed AD would affect about 9 airplanes of U.S. registry. 
The proposed inspection would take about 1 work hour per airplane, at 
an average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $720, or $80 
per airplane, 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 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-2007-27509; Directorate 
Identifier 2006-NM-201-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 11, 
2007.

[[Page 10953]]

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 that, after landing, the 
flight crew of a Model F.28 Mark 0100 airplane noted that an extreme 
difference in pedal angle was required to achieve equal braking 
action. We are issuing this AD to prevent failure of one or more 
brake control levers, which could result in uncommanded braking and 
loss of control of the airplane during takeoff, landing, or taxiing.

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 Replacement

    (f) Within 1,500 flight cycles or 12 months after the effective 
date of this AD, whichever occurs first: Perform a detailed 
inspection for excessive wear of the brake control levers and do the 
applicable corrective actions in accordance with and at the times 
specified in Section 3, ``Accomplishment Instructions,'' of Fokker 
Service Bulletin SBF100-32-142, dated August 12, 2005. Repeat the 
requirements of this paragraph thereafter for any replacement 
control lever at an interval not to exceed 12,000 flight hours after 
the installation of such a control lever. Operators should note 
that, where the service bulletin specifies immediate replacement of 
the control lever if the applicable remaining material (dimension 
X2) of the attachment hole is less than 2.0 millimeters (0.08 
inches), this AD requires replacing the control lever if dimension 
X2 is less than or equal to 2.0 millimeters.

    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.''

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, International Branch, ANM-116, 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

    (h) Dutch airworthiness directive NL-2005-011, dated August 31, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 5, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-4379 Filed 3-9-07; 8:45 am]
BILLING CODE 4910-13-P