[Federal Register Volume 69, Number 106 (Wednesday, June 2, 2004)]
[Proposed Rules]
[Pages 31053-31055]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-12399]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-302-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 
400, 500, 600, and 700 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Fokker Model F27 Mark 100, 
200, 300, 400, 500, 600, and 700 series airplanes. This proposal would 
require a one-time inspection to determine the part number of the 
engine mounting frames, brace struts, and attachment fittings; and 
related corrective action. This action is necessary to ensure the 
structural integrity of the engine-to-wing load path and prevent 
possible separation of the engine from the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by July 2, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-302-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-302-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, 
the Netherlands. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tom Groves, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1503; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact

[[Page 31054]]

concerned with the substance of this proposal will be filed in the 
Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-302-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2002-NM-302-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Civil Aviation Authority--The Netherlands (CAA-NL), which is 
the airworthiness authority for the Netherlands, notified the FAA that 
an unsafe condition may exist on certain Fokker Model F27 Mark 100, 
200, 300, 400, 500, 600, and 700 series airplanes. The CAA-NL advises 
that there have been several approved modifications to Model F27 series 
airplanes over the years that add higher weight and more powerful 
engines, increased maximum landing weights, and reduced flap settings. 
These changes result in higher loads on the engine mounts, brace 
struts, and attachment fittings. Although replacement of the engine 
mounts, brace struts, and attachment fittings with new improved, 
stronger units was part of the previous modification procedures, it has 
been determined that the original parts may have been re-installed on 
some of the modified airplanes. These modifications ensure the 
structural integrity of the engine-to-wing load path and prevent 
possible separation of the engine from the airplane.

Explanation of Relevant Service Information

    Fokker Services B.V. has issued Service Bulletin F27/54-53, dated 
February 15, 2002, which describes procedures for a one-time visual 
examination to determine the part number (PN) of the engine mounting 
frames, brace struts, and attachment fittings; and related corrective 
action. The related corrective action involves replacing incorrect 
parts on airplanes having a post-Fokker Service Bulletin F27/71-29, 
F27/71-31, F27/71-41, or F27/71-42 configuration. Service Bulletin F27/
54-53 references the following service bulletins for procedures for the 
related corrective actions:
     Fokker Service Bulletin 51-24, dated December 1, 1971; 
which describes procedures for installing a new, improved engine 
mounting frame.
     Fokker Service Bulletin F27/54-26, Revision 5, dated 
September 30, 2001; which describes procedures for installing new, 
improved, stronger brace struts and brackets.
    Accomplishment of the actions specified in Service Bulletin F27/54-
53 is intended to adequately address the identified unsafe condition. 
The CAA-NL classified this service bulletin as mandatory and issued 
Dutch airworthiness directive 2002-067, dated May 31, 2002, to ensure 
the continued airworthiness of these airplanes in the Netherlands.

FAA's Conclusions

    This airplane model is manufactured in the Netherlands and is type 
certificated for operation in the United States under the provisions of 
Sec.  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 us informed of 
the situation described above. We have examined the findings of the 
CAA-NL, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require accomplishment of 
the actions specified in Fokker Service Bulletin F27/54-53, except as 
discussed below.

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

    The Dutch airworthiness directive and Service Bulletin F27/54-53 
recommend that the one-time inspection to determine the part numbers of 
the engine mounting frames, brace struts, and attachment fittings be 
done within 6 months after the effective date/issuance of those 
documents; however, this proposed AD would require operators to do the 
one-time inspection within 24 months after the effective date of this 
AD. In developing the compliance time for this action, we considered 
the degree of urgency associated with addressing the subject unsafe 
condition as well as the availability of required parts. We have 
determined that 24 months represents an appropriate interval of time in 
which an ample number of required parts will be available to modify 
affected airplanes, if corrective action is required, without adversely 
affecting the safety of these airplanes. This change has been 
coordinated with the CAA.
    The applicability section in the Dutch airworthiness directive 
includes, in part, ``all aircraft that operate with a standard flap 
setting for landing of 26.5 degrees.'' Service Bulletin F27/54-53 
includes specific actions for airplanes that operate with a standard 
flap setting for landing of 26.5 degrees. Therefore, such airplanes do 
not require specific identification in the applicability section of 
this proposed AD.
    Service Bulletin F27/54-53 refers to a visual examination to 
determine certain P/Ns; the Dutch airworthiness directive specifies to 
``inspect'' for P/N identification. We have determined that the 
inspection should be described as a ``general visual inspection.'' Note 
1 has been included in this proposed AD to define this type of 
inspection.

Cost Impact

    We estimate that 41 airplanes of U.S. registry would be affected by 
this proposed AD, that it would take about 4 work hours per airplane to 
accomplish the proposed inspection, and that the average labor rate is 
$65 per work hour. Based on these figures, the cost impact of the 
inspection proposed by this AD on U.S. operators is estimated to be 
$10,660, or $260 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted. The cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.

[[Page 31055]]

    For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

Fokker Services B.V.: Docket 2002-NM-302-AD.

    Applicability: Model F27 Mark 100, 200, 300, 400, 500, 600, and 
700 series airplanes; certificated in any category; on which one or 
more of the modifications specified in paragraph 1.A.(1) of Fokker 
Service Bulletin F27/54-53, dated February 15, 2002, has been done.
    Compliance: Required as indicated, unless accomplished 
previously.
    To ensure the structural integrity of the engine-to-wing load 
path and prevent possible separation of the engine from the 
airplane, accomplish the following:

One-Time Inspection

    (a) Within 24 months after the effective date of this AD: Do a 
one-time general visual inspection to determine the part numbers of 
the engine mounting frames, brace struts, and attachment fittings; 
per the Accomplishment Instructions of Fokker Service Bulletin F27/
54-53, dated February 15, 2002. Do the inspection and corrective 
action per the Accomplishment Instructions of the service bulletin. 
Do the related corrective action before further flight.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Related Service Information

    Note 2: Fokker Service Bulletin F27/54-53, dated February 15, 
2002, references Fokker Service Bulletin 51-24, dated December 1, 
1971, as the appropriate source of service information for 
installing a new, improved engine mounting frame; and Fokker Service 
Bulletin F27/54-26, Revision 5, dated September 30, 2001, as the 
appropriate source of service information for installing new, 
improved, stronger brace struts and brackets.

Parts Installation

    (b) As the effective date of this AD, no person may install on 
any airplane an engine mounting frame, brace strut, or attachment 
fitting unless that part has been identified as appropriate for the 
airplane configuration, as specified in the Accomplishment 
Instructions of Fokker Service Bulletin F27/54-53, dated February 
15, 2002.

Alternative Methods of Compliance

    (c) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized 
to approve alternative methods of compliance for this AD.

    Note 3: The subject of this AD is addressed in Dutch 
airworthiness directive 2002-067, dated May 31, 2002.


    Issued in Renton, Washington, on May 20, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-12399 Filed 6-1-04; 8:45 am]
BILLING CODE 4910-13-P