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

[Federal Register Volume 63, Number 211 (Monday, November 2, 1998)]
[Rules and Regulations]
[Pages 58625-58627]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-29002]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-101-AD; Amendment 39-10847; AD 98-22-01]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Fokker Model F.28 Mark 0100 series airplanes, 
that requires a one-time visual inspection and a one-time eddy current 
and/or dye penetrant inspection of the nose landing gear (NLG) main 
fitting to detect cracking; and rework of the NLG main fitting, if 
necessary. This amendment is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this AD are intended to prevent 
cracking of the NLG main fitting, which could lead to collapse of the 
NLG during takeoff and landing and possible injury to the flightcrew 
and passengers.

DATES: Effective December 7, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 7, 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

[[Page 58626]]

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 certain Fokker Model F.28 Mark 
0100 series airplanes was published in the Federal Register on May 28, 
1998 (63 FR 29157). That action proposed to require a one-time visual 
inspection and a one-time eddy current and/or dye penetrant inspection 
of the nose landing gear (NLG) main fitting to detect cracking; and 
rework of the NLG main fitting, if necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Acknowledge Inspections Accomplished Previously

    Two commenters support the intent of the proposal but request that 
the reporting requirement of the proposed AD be revised to recognize 
inspections accomplished prior to the effective date of this AD. The 
commenters indicate that paragraph (d) of the proposed rule specifies 
that results of the inspections performed in accordance with paragraph 
(a) or (b) of the AD are to be submitted to the manufacturer within 7 
days after accomplishment of the inspections. Both commenters point out 
that operators that have accomplished the inspections previously, but 
that did not submit a report of the results to the manufacturer within 
7 days after accomplishment of the inspections, would be immediately 
out of compliance with the AD and would have to accomplish the 
inspections again in order to comply.
    The FAA concurs with the request. Therefore, the FAA has revised 
paragraph (d) of the final rule to incorporate a grace period for the 
reporting requirement. Paragraph (d) of the final rule specifies that a 
report of the inspection results must be submitted to the manufacturer, 
``Within 7 days after accomplishing the inspection required by either 
paragraph (a) or (b) of this AD, or within 7 days after the effective 
date of this AD, whichever occurs later.''

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 with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 127 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 2 work hours per airplane to accomplish 
the visual inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the visual inspection 
required by this AD on U.S. operators is estimated to be $15,240, or 
$120 per airplane.
    It will take approximately 2 work hours per airplane to accomplish 
the eddy current and/or dye penetrant inspection, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
the eddy current and/or dye penetrant inspection required by this AD on 
U.S. operators is estimated to be $15,240, or $120 per airplane.
    The cost impact figures discussed above are 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:

98-22-01  Fokker Services B.V.: Amendment 39-10847. Docket No. 98-
NM-101-AD.

    Applicability: Model F.28 Mark 0100 series airplanes, equipped 
with Messier-Dowty Nose Landing Gear (NLG) having part number (P/N) 
201071001 or P/N 201071002, on which the NLG main fitting has not 
been overhauled in accordance with Component Maintenance Manual 32-
20-51; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (e) 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 NLG main fitting, which could lead to 
collapse of the NLG during takeoff and landing and possible injury 
to the flightcrew and passengers, accomplish the following:
    (a) Perform a one-time visual inspection to detect cracking of 
the NLG main fitting, in accordance with Fokker Service Bulletin 
SBF100-32-112, dated November 14, 1997, at the applicable time 
specified in either paragraph (a)(1) or (a)(2) of this AD. If any 
cracking is found, prior to further flight, accomplish the 
requirements of paragraph (b) of this AD.
    (1) 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 8,000 total flight cycles, or within 90 days 
after the effective date of this AD, whichever occurs later.
    (2) 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.

[[Page 58627]]

    (b) Perform a one-time eddy current and/or dye penetrant 
inspection to detect cracking of the NLG main fitting, in accordance 
with Messier-Dowty Service Bulletin F100-32-92, dated November 14, 
1997, at the applicable time specified in either paragraph (b)(1) or 
(b)(2) of this AD. Accomplishment of the inspection required by 
paragraph (b) of this AD, if accomplished prior to the inspection 
required by paragraph (a) of this AD, terminates the inspection 
requirement of paragraph (a) of this AD.
    (1) 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 8,000 total flight cycles, or within 180 days 
after the effective date of this AD, whichever occurs later.
    (2) For airplanes that have accumulated 15,000 or more total 
flight cycles as of the effective date of this AD: Inspect within 60 
days after the effective date of this AD.
    (c) If any crack is detected during the inspection required by 
paragraph (b) of this AD, prior to further flight, rework the NLG 
main fitting in accordance with Messier-Dowty Service Bulletin F100-
32-92, dated November 14, 1997.
    (d) Within 7 days after accomplishing the inspection required by 
either paragraph (a) or (b) of this AD, or within 7 days after the 
effective date of this AD, whichever occurs later, submit a report 
of the inspection results (both positive and negative findings) to 
Fokker Services B.V., Technical Support Department, P.O. Box 75047, 
1117 ZN Schiphol Airport, the Netherlands. 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.
    (e) 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 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.

    (f) 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.
    (g) Except as provided by paragraph (d) of this AD, the actions 
shall be done in accordance with Fokker Service Bulletin SBF100-32-
112, dated November 14, 1997, and Messier-Dowty Service Bulletin 
F100-32-92, dated November 14, 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 BLA 1997-116 (A), dated November 28, 1997.

    (h) This amendment becomes effective on December 7, 1998.

    Issued in Renton, Washington, on October 13, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-29002 Filed 10-30-98; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:56:45.282349+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

68f7c69912989bc03ffee6f36709ae335d5ce26e44aad05019fd0511b2c69fec

Text SHA-256

21b9197a85a8d895f7fbcc05fa287963d6ec6eac3cbf843fe15a2fd48b785ff6