[Federal Register Volume 67, Number 35 (Thursday, February 21, 2002)]
[Rules and Regulations]
[Pages 7945-7947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3850]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-332-AD; Amendment 39-12660; AD 2002-04-03]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F27 Mark 050 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Fokker Model F27 Mark 050 series airplanes. 
This action requires reinforcement of the structural provisions for the 
Global Positioning System (GPS) antenna by replacement of existing 
fasteners with new fasteners, and installation of conical washers and a 
doubler plate at stringer 26, as applicable. This action is necessary 
to prevent cracking of the structure of the fuselage pressure vessel in 
the area of the GPS antenna, leading to reduced structural integrity of 
the fuselage pressure vessel, which could result in depressurization of 
the airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective March 8, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 8, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before March 25, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-332-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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. 2001-NM-332-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 for Windows or 
ASCII text.
    The service information referenced in this AD 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; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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: The Civil Aviation Authority--The 
Netherlands (CAA-NL), which is the airworthiness

[[Page 7946]]

authority for the Netherlands, notified the FAA that an unsafe 
condition may exist on certain Fokker Model F27 Mark 050 series 
airplanes. The CAA-NL advises that, during a product review, Fokker 
Services discovered that the structural provisions for the Global 
Positioning System (GPS) antenna do not meet pertinent structural 
strength requirements. Failure to meet these structural strength 
requirements could lead to reduced fatigue life of the GPS antenna's 
structural provisions. This condition, if not corrected, could result 
in cracking of the structure of the fuselage pressure vessel in the 
area of the GPS antenna, reduced structural integrity of the fuselage 
pressure vessel, and possible depressurization of the airplane.

Explanation of Relevant Service Information

    Fokker Services B.V. has issued Fokker Service Bulletin SBF50-53-
055, dated May 25, 2001. This service bulletin describes procedures for 
reinforcement of the structural provisions for the GPS antenna by 
replacement of existing fasteners with new fasteners. For certain 
airplanes, the reinforcement of the structural provisions for the GPS 
antenna also necessitates installation of conical washers and a doubler 
plate at stringer 26. Accomplishment of the applicable actions 
specified in the service bulletin is intended to adequately address the 
identified unsafe condition. The CAA-NL classified this service 
bulletin as mandatory and issued Dutch airworthiness directive 2001-
092, dated July 31, 2001, in order to assure the continued 
airworthiness of these airplanes in the Netherlands.

FAA's Conclusions

    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 
21.19) 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. The FAA has 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 the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to prevent cracking of the structure of the fuselage 
pressure vessel in the area of the GPS antenna, which could result in 
reduced structural integrity of the fuselage pressure vessel and 
consequent depressurization of the airplane. This AD requires 
accomplishment of the actions specified in the service bulletin 
described previously, except as discussed below.

Differences Between AD, Service Information, and Foreign 
Airworthiness Directive

    The service bulletin and foreign airworthiness directive recommend 
that the actions in the service bulletin be accomplished within 6,000 
flight cycles after installation of the structural provisions for the 
GPS antenna. The FAA finds, however, that such a compliance time could 
ground airplanes upon the effective date of this AD. Therefore, this AD 
provides a grace period of 60 days after the effective date of this AD 
for airplanes that have passed the 6,000-flight-cycle compliance 
threshold.

Cost Impact

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this rule 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    Should an affected airplane that is subject only to the replacement 
of fasteners be imported and placed on the U.S. Register in the future, 
it would require approximately 2 work hours to accomplish the required 
reinforcement, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of this AD would be $120 per airplane.
    Should an affected airplane that is subject to both the replacement 
of fasteners and the installation of conical fasteners and a doubler be 
imported and placed on the U.S. Register in the future, it would 
require approximately 4 work hours to accomplish the required 
reinforcement, at an average labor rate of $60 per work hour. Required 
parts would cost approximately $142 per airplane. Based on these 
figures, the cost impact of this AD would be $382 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
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 under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-332-AD.''

[[Page 7947]]

The postcard will be date-stamped and returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

2002-04-03  Fokker Services B.V.: Amendment 39-12660. Docket 2001-
NM-332-AD.

    Applicability: Model F27 Mark 050 series airplanes, as listed in 
Fokker Service Bulletin SBF50-53-055, dated May 25, 2001, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent cracking of the structure of the fuselage pressure 
vessel in the area of the Global Positioning System (GPS) antenna, 
leading to reduced structural integrity of the fuselage pressure 
vessel, which could result in depressurization of the airplane, 
accomplish the following:

Reinforcement of Structural Provisions for GPS Antenna

    (a) Within 6,000 flight cycles since installation of structural 
provisions for the GPS antenna per Fokker Service Bulletin SBF50-34-
047, or Fokker Engineering Report FS-N399 or FS-N364, as applicable; 
or within 60 days after the effective date of this AD; whichever 
occurs later: Reinforce the structural provisions for the GPS 
antenna by replacing existing fasteners with new fasteners, and 
installing conical washers and a doubler plate at stringer 26, as 
applicable, per Fokker Service Bulletin SBF50-53-055, dated May 25, 
2001.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The actions shall be done in accordance with Fokker Service 
Bulletin SBF50-53-055, dated May 25, 2001. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in Dutch 
airworthiness directive 2001-092, dated July 31, 2001.

Effective Date

    (e) This amendment becomes effective on March 8, 2002.

    Issued in Renton, Washington, on February 11, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 02-3850 Filed 2-20-02; 8:45 am]
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