[Federal Register Volume 63, Number 219 (Friday, November 13, 1998)]
[Proposed Rules]
[Pages 63423-63425]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30333]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-276-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 63424]]

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Fokker Model F.28 Mark 
0070 and 0100 series airplanes. This proposal would require a one-time 
visual inspection to detect discrepancies of the components of the 
torque link apex joint and shimmy damper attachments of the main 
landing gear (MLG), and repair or replacement of any discrepant 
component with a new or serviceable component. This proposal is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
the proposed AD are intended to prevent heavy vibration and possible 
damage to the components of the MLG, and consequent reduced 
controllability of the airplane during takeoff and landing.

DATES: Comments must be received by December 14, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-276-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.
    The service information referenced in the proposed rule may be 
obtained from Fokker Services B.V., Technical Support Department, P.O. 
Box 75047, 1117 ZN Schiphol Airport, the Netherlands. This information 
may be examined at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington.

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:

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 notice may be changed in 
light of the comments received.
    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 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-NM-276-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. 98-NM-276-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    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.28 Mark 0070 and 0100 
series airplanes. The RLD advises that it received a report of heavy 
vibration coming from the main landing gear (MLG) during landing. 
Investigation revealed that the cause of the heavy vibration was 
attributed to the nut of the apex bolt becoming detached from the apex 
pin, which resulted in disconnection of the upper and lower torque 
links of the right-hand MLG at the apex joint. Subsequent 
investigations of other Fokker Model F.28 series airplanes, equipped 
with Menasco MLG's, revealed loss of torque of the apex pin of the 
torque links and, in some cases, loss of torque of the shimmy damper 
attachment bolts. These conditions, if not corrected, could result in 
heavy vibration and possible damage to the components of the MLG, and 
consequent reduced controllability of the airplane during takeoff or 
landing.

Explanation of Relevant Service Information

    Fokker has issued Service Bulletin SBF100-32-113, dated May 28, 
1998, which describes procedures for a one-time visual inspection to 
detect discrepancies of the components of the torque link apex joint 
and shimmy damper attachments of the MLG, and repair or replacement of 
any discrepant component with a new or serviceable component. 
Discrepancies may include incorrect positioning of the apex pin, 
misalignment of the slotted locking nut, loss of torque of the bolts, 
or damage to the locking plate and apex bolt. The service bulletin also 
recommends informing Fokker Services of inspection results.
    Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition. The RLD 
classified this service bulletin as mandatory and issued Dutch 
airworthiness directive BLA 1998-058 (A), dated May 29, 1998, in order 
to assure the continued airworthiness of these airplanes in the 
Netherlands.

Other Relevant Rulemaking

    On October 7, 1998, the FAA issued AD 98-21-33, amendment 39-10841 
(63 FR 55527, October 16, 1998), applicable to all Fokker Model F.28 
Mark 0070 and 0100 series airplanes, to require a one-time inspection 
of the torque links of the MLG assemblies to determine if the lockwire 
is present on the apex bolt, and corrective action, if necessary. 
However, this proposed AD would not affect the current requirements of 
that previously issued AD.

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 
21.29) 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 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 the service bulletin described previously.

Cost Impact

    The FAA estimates that 131 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per

[[Page 63425]]

airplane to accomplish the proposed inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be $15,720, 
or $120 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.

Regulatory Impact

    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 98-NM-276-AD.

    Applicability: Model F.28 Mark 0070 and 0100 series airplanes, 
as listed in Fokker Service Bulletin SBF100-32-113, dated May 28, 
1998; 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 (d) 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 heavy vibration and possible damage to the components 
of the main landing gear (MLG), and consequent reduced 
controllability of the airplane during takeoff or landing, 
accomplish the following:
    (a) Within 45 days after the effective date of this AD, perform 
a one-time visual inspection to detect discrepancies of the 
components of the torque link apex joint and shimmy damper 
attachments of the MLG, in accordance with Fokker Service Bulletin 
SBF100-32-113, dated May 28, 1998. If any discrepancy is detected, 
prior to further flight, repair or replace any discrepant component 
with a new or serviceable component, in accordance with the service 
bulletin.

    Note 2: In paragraph 2.F.(10) of the Accomplishment Instructions 
of Fokker Service Bulletin SBF100-32-113, dated May 28, 1998, the 
parenthetical phrase that recommends the size of torque wrench to 
use, should read ``* * * (0 to 75 lbf ft),'' rather than ``* * * (0 
to 75 lbf in)''.

    (b) Submit a report of the inspection findings (positive or 
negative) to Fokker Services B.V., Technical Services, Attn.: 
Manager Airline Support, P.O. Box 75047, 1117 ZN Schiphol-Oost, the 
Netherlands; Fax No. 3120605200; at the time specified in paragraph 
(b)(1) or (b)(2) of this AD, as applicable. Information collection 
requirements contained in this regulation have been approved by the 
Office of Management and Budget (OMB) under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have 
been assigned OMB Control Number 2120-0056.

    (1) For airplanes on which the inspection required by paragraph 
(a) of this AD is accomplished after the effective date of this AD: 
Submit a report within 10 days after accomplishing the inspection 
required by paragraph (a) of this AD.
    (2) For airplanes on which the inspection required by paragraph 
(a) of this AD has been accomplished prior to the effective date of 
this AD: Submit a report within 30 days after the effective date of 
this AD.
    (c) As of the effective date of this AD, no person shall install 
on any airplane a Menasco MLG having part number (P/N) 41050-5, -6, 
-7, or -8; or P/N 41060-1 or -2; unless it has been inspected in 
accordance with paragraph (a) of this AD.
    (d) 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.

    (e) Special flight permits may be issued in accordance with 
sections 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.

    Note 4: The subject of this AD is addressed in Dutch 
airworthiness directive BLA 1998-058(A), dated May 29, 1998.

    Issued in Renton, Washington, on November 5, 1998.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-30333 Filed 11-12-98; 8:45 am]
BILLING CODE 4910-13-P