Airworthiness Directives; Fokker Model F.27 Mark 050 Series Airplanes

[Federal Register Volume 64, Number 202 (Wednesday, October 20, 1999)]
[Rules and Regulations]
[Pages 56422-56424]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26933]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-225-AD; Amendment 39-11379; AD 99-21-33]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.27 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), 
applicable to certain Fokker Model F.27 Mark 050 series airplanes. This 
action requires a one-time inspection to detect improper installation 
of countersunk screws used to attach the access panels to the bottom 
skin of the center wing; and corrective action, if necessary. This 
amendment is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified in this AD are intended to detect and correct such improper 
installation, which could result in fatigue cracking of the bottom skin 
of the center wing and consequent reduced structural integrity of the 
airplane.

DATES: Effective November 4, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 4, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before November 19, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-225-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Rijksluchtvaartdienst (RLD), which is 
the airworthiness authority for the Netherlands, notified the FAA that 
an unsafe condition may exist on certain Fokker Model F.27 Mark 050 
series airplanes. The RLD advises that, on a number of airplanes on the 
production line, the heads of countersunk screws were found not to seat 
properly in their countersinkings. The affected screws are used in the 
attachment of access panels of the bottom skin of the center wing. This 
condition, if not corrected, could result in fatigue cracking of the 
bottom skin of the center wing and consequent reduced structural 
integrity of the airplane.

Explanation of Relevant Service Information

    Fokker has issued Service Bulletin SBF50-57-015, dated February 28, 
1996, which describes procedures for a one-time detailed visual 
inspection to detect improper installation (excessive gap) of the 
countersunk screws in the access covers of the bottom skin of the 
center wing.
    Fokker has also issued Service Bulletin SBF50-57-018, dated 
February 28, 1996, which describes procedures

[[Page 56423]]

for reaming of the fastener holes and an eddy current inspection to 
detect cracks in the bottom skin of the center wing. This service 
bulletin also describes procedures to repair any cracking that is 
found.
    The RLD classified these service bulletins as mandatory and issued 
Dutch airworthiness directive 1996-042 (A), dated April 29, 1996, in 
order to assure 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 21.19) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the RLD has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
RLD, 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 registered 
in the United States, this AD is being issued to detect and correct 
improper installation of countersunk screws in the attachment of access 
panels of the bottom skin of the center wing, which could result in 
fatigue cracking of the bottom skin and consequent reduced structural 
integrity of the airplane. This AD requires accomplishment of the 
actions specified in the service bulletins described previously.

Differences Between Rule and Service Bulletin

    Operators should note that, although Fokker Service Bulletin SBF50-
57-018 specifies that the manufacturer may be contacted for disposition 
of certain repair conditions, this AD would require the repair of those 
conditions to be accomplished in accordance with a method approved by 
the FAA.

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 be imported and placed on the U.S. 
Register in the future, it would require approximately 6 work hours to 
accomplish the required inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$360 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.
    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 99-NM-225-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

99-21-33  Fokker Services B.V.: Amendment 39-11379. Docket 99-NM-
225-AD.

    Applicability: Model F.27 Mark 050 series airplanes, serial 
numbers 20103 through 20263 inclusive; 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

[[Page 56424]]

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 (c) 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 detect and correct improper installation of countersunk 
screws in the attachment of access panels of the bottom skin of the 
center wing, which could result in fatigue cracking of the bottom 
skin of the center wing and consequent reduced structural integrity 
of the airplane, accomplish the following:

Initial Inspection

    (a) Prior to the accumulation of 24,000 total flight cycles, 
perform a one-time detailed visual inspection to detect improper 
installation (excessive gap) of the countersunk screws used to 
attach the access panels to the bottom skin of the center wing, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF50-57-015, dated February 28, 1996.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Inspection and Corrective Action

    (b) If any improper installation (excessive gap) is found during 
the inspection required by paragraph (a) of this AD: Prior to the 
accumulation of 24,000 total flight cycles, ream the fastener holes 
in the rabbet of the bottom skin of the center wing and perform an 
eddy current inspection for cracking of the fastener holes in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF50-57-018, dated February 28, 1996.

Repair

    (1) For any fastener hole for which no crack is found during the 
eddy current inspection: Prior to further flight; accomplish 
corrective actions for the fastener hole, in accordance with Step C. 
of Repair Scheme No. 1 of Fokker Service Bulletin SBF50-57-018, 
dated February 28, 1996.
    (2) For any fastener hole for which a crack is found during the 
eddy current inspection: Prior to further flight; repair and re-
inspect the fastener hole, in accordance with Steps A. and B. of 
Repair Scheme No. 1 of Fokker Service Bulletin SBF50-57-018, dated 
February 28, 1996. For any crack that is outside the limits 
specified in the service bulletin, prior to further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Rijksluchtvaartdienst (RLD) (or its delegated agent). For a 
repair method to be approved by the Manager, International Branch, 
ANM-116, as required by this paragraph, the Manager's approval 
letter must specifically reference this AD.

Alternative Methods of Compliance

    (c) 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, FAA, 
Transport Airplane Directorate. 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 3: 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

    (d) 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

    (e) Except as provided by paragraph (b)(2) of this AD, the 
actions shall be done in accordance with Fokker Service Bulletin 
SBF50-57-015, dated February 28, 1996, and Fokker Service Bulletin 
SBF50-57-018, dated February 28, 1996. 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 4: The subject of this AD is addressed in Dutch 
airworthiness directive 1996-042 (A), dated April 29, 1996.

    (f) This amendment becomes effective on November 4, 1999.

    Issued in Renton, Washington, on October 8, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-26933 Filed 10-19-99; 8:45 am]
BILLING CODE 4910-13-P

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