[Federal Register Volume 66, Number 124 (Wednesday, June 27, 2001)]
[Proposed Rules]
[Pages 34132-34134]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-16053]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-23-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 1000, 2000, 
3000, and 4000 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all Fokker Model F.28 Mark 1000, 
2000, 3000, and 4000 series airplanes. This proposal would require a 
one-time eddy current inspection for cracks of the fuselage butt joint 
which is forward of the emergency exits on the left- and right-hand 
sides of the airplane at the level of stringers 27/48. This proposal 
would also require repair of any cracks detected. This action is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign airworthiness authority. This action is necessary to 
detect and correct cracks in the area of the emergency escape hatches, 
which, if undetected, could

[[Page 34133]]

result in depressurization during flight, possibly leading to 
structural failure of the airplane. This action is intended to address 
the identified unsafe condition.

DATES: Comments must be received by July 27, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket Number 2001-NM-23-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 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: 
<a href="/cdn-cgi/l/email-protection#7940541817145417090b141a1614141c170d391f1818571e160f"><span class="__cf_email__" data-cfemail="dde4f0bcb3b0f0b3adafb0beb2b0b0b8b3a99dbbbcbcf3bab2ab">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-23-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 the proposed rule 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.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> 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 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-23-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 Number 2001-NM-23-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 a crack was found 
in the fuselage skin in a bonded doubler at stringer 48 during regular 
maintenance of a Model F.28 Mark 1000 series airplane. The airplane had 
accumulated 56,000 total flight cycles when the crack was discovered. 
Subsequent investigation revealed that the crack began at a scratch, 
which may have occurred during production, on the bonded doubler at the 
edge of the bonded lower skin. This condition, if not corrected, could 
result in depressurization during flight, possibly leading to 
structural failure of the airplane.

Explanation of Relevant Service Information

    Fokker has issued Service Bulletin SBF28/53-148, dated August 15, 
2000, which describes procedures for conducting a one-time eddy current 
inspection for cracks of the fuselage butt joint forward of the 
emergency exits on the left- and right-hand sides of the airplane at 
the level of stringers 27/48 and reporting the findings to Fokker. The 
RLD classified this service bulletin as mandatory and issued Dutch 
airworthiness directive 2000-151, dated November 30, 2000, in order to 
assure the continued airworthiness of these airplanes in the 
Netherlands. If any cracks are found as a result of the inspection, 
repair is to be conducted in a manner approved by the FAA or the RLD.

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 Sec. 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, 
except as discussed below. The proposed AD also would require reporting 
of the results (positive or negative) to the FAA.

Differences Between Proposed Rule and Foreign Airworthiness 
Directive

    Operators should note that, although the Dutch airworthiness 
directive specifies that the manufacturer may be contacted for 
disposition of certain repair conditions, this proposal would require 
the repair of those conditions to be accomplished per a method approved 
by either the FAA or the RLD (or a delegated agent of the RLD). In 
light of the type of repair that would be required to address the 
identified unsafe condition, and in consonance with existing bilateral 
airworthiness agreements, the FAA has determined that, for this 
proposed AD, a repair approved by either the FAA or the RLD would be 
acceptable for compliance with this proposed AD.

Cost Impact

    The FAA estimates that 23 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per airplane to accomplish the proposed

[[Page 34134]]

eddy current 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 $2,760, 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 proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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 2001-NM-23-AD.
    Applicability: All Model F.28 Mark 1000, 2000, 3000, and 4000 
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 (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 detect and correct cracks in the area of the emergency escape 
hatches, which, if undetected, could result in depressurization 
during flight, possibly leading to structural failure of the 
airplane, accomplish the following:

Inspection

    (a) Prior to the accumulation of 30,000 total flight cycles, or 
within 12 months after the effective date of this AD, whichever 
occurs later: Perform a one-time eddy current inspection to detect 
cracks of the fuselage butt joint forward of the emergency hatches 
on the left- and right-hand sides of the airplane at the level of 
stringers 27/48, in accordance with the Accomplishment Instructions 
of Fokker Service Bulletin SBF28/53-148, dated August 15, 2000.

Repair

    (b) If any crack is found during the inspection required by 
paragraph (a) of this AD: Prior to further flight, repair the crack 
per a method approved by either the Manager, International Branch, 
ANM-116, FAA, Transport Airplane Directorate; or the 
Rijksluchtvaartdienst (or its delegated agent).

Reporting

    (c) Submit a report of inspection findings (both positive and 
negative) to Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands; and to Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056; fax (425) 227-1320. The report is to 
be submitted at the applicable time specified in paragraph (c)(1) or 
(c)(2) of this AD. The report must include the inspections results, 
a description of any discrepancies found, the airplane serial 
number, and the number of landings and flight hours on the airplane. 
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 is accomplished after 
the effective date of this AD: Submit a report of findings within 10 
days after performing the inspection required by paragraph (a) of 
this AD.
    (2) For airplanes on which the inspection was accomplished prior 
to the effective date of this AD: Submit a report of findings within 
10 days after the effective date of this AD.

Alternative Methods of Compliance

    (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. 
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

    (e) 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.

    Issued in Renton, Washington, on June 20, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-16053 Filed 6-26-01; 8:45 am]
BILLING CODE 4910-13-U


</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>