Airworthiness Directives; Fokker Model F28 Mark 0100 Series Airplanes

[Federal Register Volume 62, Number 149 (Monday, August 4, 1997)]
[Rules and Regulations]
[Pages 41839-41841]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-20440]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-149-AD; Amendment 39-10100; AD 97-16-08]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F28 Mark 0100 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 F28 Mark 0100 series airplanes. This 
action requires a one-time inspection to detect fatigue cracking of the 
hinges of the cargo doors, and repair, if necessary. This amendment is 
prompted by reports indicating that, during inspections of the cargo 
door area, fatigue cracking of hinges of the cargo doors was detected. 
The actions specified by the proposed AD are intended to detect and 
correct such cracking, which could result in structural failure of the 
cargo doors, and consequent rapid decompression of the airplane and 
possible separation of the cargo doors from the airplane during flight.

DATES: Effective August 19, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 19, 1997.
    Comments for inclusion in the rules docket must be received on or 
before October 3, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 97-NM-149-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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 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: Tim Dulin, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton,

[[Page 41840]]

Washington 98055-4056; telephone (425) 227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Rijksluchtvaartdienst (RLD), which is 
the airworthiness authority for the Netherlands, recently notified the 
FAA that an unsafe condition may exist on certain Fokker Model F28 Mark 
0100 series airplanes. The RLD advises that it has received reports 
indicating that, during scheduled visual inspections of the cargo door 
area, fatigue cracking of the hinges of the forward, center, and rear 
cargo doors were found. This cracking occurred much earlier than 
anticipated by fatigue analysis and test results. Therefore, the 
threshold for inspection of the cargo door hinges specified in the 
Airworthiness Limitations Items (ALI) and Maintenance Review Board 
(MRB) task numbers 523052-00-02 and 523052-00-03 may need to be 
adjusted. Investigation is continuing to determine if other factors 
(such as a jamming cargo net at the door hinge, a cargo door that slams 
against the fuselage when it is opened, etc.) may have contributed to 
the cracking of the hinges.
    Fatigue cracking of the hinges of the cargo doors, if not detected 
and corrected in a timely manner, could result in structural failure of 
the cargo doors, and consequent rapid decompression of the airplane and 
possible separation of the cargo doors from the airplane during flight.

Explanation of Relevant Service Information

    Fokker has issued Service Bulletin SBF100-52-061, dated September 
28, 1996, which describes procedures for a one-time inspection to 
detect fatigue cracking of the hinges of the cargo doors. The service 
bulletin also provides a form for operators to report the results of 
the one-time inspection. The RLD classified this service bulletin as 
mandatory and issued Dutch airworthiness directive (BLA) 1996-125 (A), 
dated September 30, 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 
section 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 require a one-time 
inspection to detect fatigue cracking of the hinges of the cargo doors, 
and repair, if necessary. This AD also requires that operators submit a 
report of the findings of the one-time inspection required by this 
action to the airplane manufacturer. The information obtained from 
these reports will enable the manufacturer to determine if other 
factors may have contributed to the fatigue cracking of the hinges. The 
inspections are required to be accomplished in accordance with the 
service bulletin described previously. Repair of any fatigue cracking 
detected, is required to be accomplished in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    None of the Model F28 Mark 0100 series 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 2 work hours to 
accomplish the required actions, at an average labor charge of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$120 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 97-NM-149-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)

[[Page 41841]]

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:

97-16-08 Fokker: Amendment 39-10100. Docket 97-NM-149-AD.

    Applicability: Model F28 Mark 0100 series airplanes, serial 
numbers 11244 through 11474 inclusive, equipped with small cargo 
doors having hinge assemblies having part numbers A28410-405, 
A28410-407, and/or D28410-409; 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 (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 fatigue cracking of the hinges, which 
could result in rapid decompression of the airplane and separation 
of the cargo doors during flight; accomplish the following:
    (a) Prior to the accumulation of 8,000 total flight cycles, or 
within 5 months after the effective date of this AD, whichever 
occurs later: Perform a one-time inspection to detect fatigue 
cracking of the hinges of the forward, center, and aft cargo doors, 
in accordance with Fokker Service Bulletin SBF100-52-061, dated 
September 28, 1996. Prior to further flight, repair any cracking 
detected, in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (b) Within 10 days after accomplishing the inspection required 
by paragraph (a) of this AD, submit a report of the inspection 
results to Fokker Services, Attn: Manager, Service Engineering--Jet, 
P. O. Box 75047, 1117 ZN Schiphol-Oost, 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.
    (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, Standardization Branch, ANM-113. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Standardization Branch, ANM-113.
    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (d) 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.
    (e) The actions shall be done in accordance with Fokker Service 
Bulletin SBF100-52-061, dated September 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., 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.
    (f) This amendment becomes effective on August 19, 1997.

    Issued in Renton, Washington, on July 29, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-20440 Filed 8-1-97; 8:45 am]
BILLING CODE 4910-13-U

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