Airworthiness Directives; Fokker Model F28 Mark 0070 and Mark 0100 Series Airplanes

[Federal Register Volume 63, Number 28 (Wednesday, February 11, 1998)]
[Rules and Regulations]
[Pages 6844-6846]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3261]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-264-AD; Amendment 39-10322; AD 98-04-09]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F28 Mark 0070 and Mark 
0100 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

[[Page 6845]]

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series 
airplanes, that requires a one-time visual inspection to detect 
cracking of the brake torque tube lever, and corrective action, if 
necessary. This amendment is prompted by the issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this AD are intended to prevent 
failure of the brake torque tube lever, which could result in a 
disconnection between the brake pedal and brake system, and consequent 
reduced directional controllability of the airplane during landing.

DATES: Effective March 18, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 18, 1998.

ADDRESSES: The service information referenced in this AD 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 Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Fokker Model F28 Mark 0070 and 
Mark 0100 series airplanes was published in the Federal Register on 
November 28, 1997 (62 FR 63294). That action proposed to require a one-
time visual inspection to detect cracking of the brake torque tube 
lever, and corrective action, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    Two commenters support the proposed rule. One commenter states that 
it has already accomplished the proposed inspection.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 131 Fokker Model F28 Mark 0070 and Mark 0100 
series airplanes of U.S. registry will be affected by this AD, that it 
will take approximately 3 work hours per airplane to accomplish the 
required inspection, and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of the inspection 
required by this AD on U.S. operators is estimated to be $23,580, or 
$180 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the 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 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:

98-04-09  Fokker: Amendment 39-10322. Docket 97-NM-264-AD.

    Applicability: All Model F28 Mark 0070 and Mark 0100 series 
airplanes, 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 failure of the captain's left-hand brake torque tube 
lever, which could result in a disconnection between the captain's 
left-hand brake pedal and left-hand brake system, and consequent 
reduced directional controllability of the airplane during landing, 
accomplish the following:
    (a) Perform a one-time visual inspection using a mirror or 
borescope to detect cracking of the brake torque tube lever having 
part number (P/N) D75669-001, in accordance with Fokker Service 
Bulletin SBF100-32-108, dated February 7, 1997, at the time 
specified in paragraph (a)(1) or (a)(2), as applicable, of this AD. 
If any crack is detected, prior to further flight, replace either 
the lever or the entire assembly with a new or serviceable 
component, in accordance with the Accomplishment Instructions of the 
service bulletin.
    (1) For airplanes that have accumulated 15,000 or more total 
flight cycles as of the effective date of this AD: Inspect within 30 
days after the effective date of this AD.
    (2) For airplanes that have accumulated fewer than 15,000 total 
flight cycles as of the effective date of this AD: Inspect prior to 
the accumulation of 10,000 total flight cycles, or within 2 months 
after the effective date of this AD, whichever occurs later.
    (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, FAA, 
Transport Airplane Directorate. Operators

[[Page 6846]]

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.

    (c) 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.
    (d) The actions shall be done in accordance with Fokker Service 
Bulletin SBF100-32-108, dated February 7, 1997. 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., Technical Support Department, 
P.O. Box 75047, 1117 ZN Schiphol Airport, 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 1997-025(A), dated February 28, 1997.

    (e) This amendment becomes effective on March 18, 1998.

    Issued in Renton, Washington, on February 4, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-3261 Filed 2-10-98; 8:45 am]
BILLING CODE 4910-13-U

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T05:06:11.960584+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

b9b2b323f5025a2a7c79925429e9bf0009ef857c0fae8237d782a73b0a86dcee

Text SHA-256

181f8976aa9db693497bc86e492deb05b971217e3f97d92b4b3494afa2565178