[Federal Register Volume 60, Number 238 (Tuesday, December 12, 1995)]
[Rules and Regulations]
[Pages 63615-63617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-29301]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-213-AD; Amendment 39-9446; AD 95-25-02]


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 inspection(s) to detect cracks of the fuselage-mounted 
half of hinge assemblies of the small cargo door, and replacement of 
any cracked hinge assembly with a new hinge assembly. This amendment is 
prompted by a report that the hinges of the small cargo door on these 
airplanes are made of a material that is sensitive to stress corrosion 
cracking. The actions specified in this AD are intended to prevent 
failure of the hinges of the small cargo door due to stress corrosion 
cracking, which could result in opening and/or separation of the door 
while the airplane is in flight, and resultant rapid decompression and/
or structural damage to the airplane.

DATES: Effective December 27, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 27, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before February 12, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-213-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, 
Virginia 22314. 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, Washington 98055-4056; telephone (206) 
227-2141; fax (206) 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 Model F28 Mark 0100 
series 

[[Page 63616]]
airplanes. The RLD advises that the hinges of the small cargo door on 
these airplanes are made of aluminum AL2024-T4, which is a material 
that is sensitive to stress corrosion cracking. Stress corrosion 
cracking in the hinge of the small cargo door could result in the 
failure of the hinge. If the hinge fails, the small cargo door could 
open and/or separate while the airplane is in flight, which could 
result in rapid decompression and/or structural damage to the airplane.
    Fokker has issued Service Bulletin SBF100-52-048, dated March 5, 
1993, which describes procedures for performing a one-time high-
frequency eddy current (HFEC) inspection to detect cracks in the 
fuselage mounted half of the hinge assemblies, having part numbers (P/
N) A28410-405 and P/N A28410-407, of the small cargo door. Fokker has 
also issued Service Bulletin SBF100-52-055, dated July 20, 1994, which 
describes inspection procedures identical to those specified in Service 
Bulletin SBF100-52-048; however, the inspections would be conducted 
repetitively, if no cracks are detected. Additionally, Fokker has 
issued Service Bulletin SBF100-52-043, dated June 12, 1995, which 
describes procedures for replacement of any cracked hinge assembly with 
a new hinge assembly having P/N D28410-409. These new hinges are made 
of aluminum AL7075-T73, which is much less sensitive to stress 
corrosion cracking than the material used in the existing hinges. In 
addition, the radii between the lugs were increased, and the web plate 
thickness was increased for the door-mounted part, to provide better 
fatigue resistance. The RLD classified these service bulletins as 
mandatory and issued Dutch airworthiness directive BLA 93-036/2 (A) in 
order to assure the continued airworthiness of these airplanes in the 
Netherlands.
    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.
    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 prevent separation or 
opening of the small cargo door while the airplane is in flight, which 
could result in rapid decompression and/or structural damage to the 
airplane. This AD requires HFEC inspection(s) to detect cracks of the 
fuselage-mounted half of certain hinge assemblies of the small cargo 
door, and replacement of any cracked hinge assembly with a certain new 
hinge assembly. The actions are required to be accomplished in 
accordance with the service bulletins described previously.
    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.
    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, 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 94-NM-213-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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: 

[[Page 63617]]


PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-25-02  Fokker: Amendment 39-9446. Docket 94-NM-213-AD.

    Applicability: Model F28 Mark 0100 series airplanes, serial 
numbers 11244 through 11408 inclusive, equipped with small cargo 
doors having hinges with part numbers (P/N) A28410-405 and/or P/N 
A28410-407; 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 use the authority 
provided in paragraph (d) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the hinges of the small cargo door due to 
stress corrosion cracking, which could result in rapid decompression 
and/or structural damage to the airplane, accomplish the following:
    (a) Within 36 months since date of manufacture of the airplane 
or within 3 months after the effective date of this AD, whichever 
occurs later, perform a high frequency eddy current (HFEC) 
inspection to detect cracks of the fuselage-mounted half of the 
hinge assemblies of the small cargo doors, in accordance with Fokker 
Service Bulletin SBF100-52-048, dated March 5, 1993.
    (1) If no cracks are detected, thereafter repeat the HFEC 
inspections at intervals not to exceed 6 months, in accordance with 
Fokker Service Bulletin SBF100-52-055, dated July 20, 1994.
    (2) If any crack is detected during any inspection required by 
paragraph (a) or (a)(1) of this AD, prior to further flight, except 
as provided in the ``NOTE'' of paragraph 2.C. of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-52-055, dated July 
20, 1994, replace the hinge assembly with a new hinge assembly 
having P/N D28410-409. The replacement shall be done in accordance 
with Fokker Service Bulletin SBF100-52-043, dated June 12, 1995.
    (b) Replacement of the hinge assembly with a new hinge assembly 
having P/N D28410-409, in accordance with Fokker Service Bulletin 
SBF100-52-043, dated June 12, 1995, constitutes terminating action 
for the requirements of this AD for that small cargo door.
    (c) As of the effective date of this AD, no person shall install 
a hinge assembly having P/N A28410-405 or -407, on any airplane, 
unless it has been previously inspected and found to be crack-free, 
in accordance with Fokker Service Bulletin SBF100-52-055, dated July 
20, 1994.
    (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, Standardization Branch, ANM-113, 
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, 
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.

    (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.
    (f) The inspections shall be done in accordance with Fokker 
Service Bulletin SBF100-52-048, dated March 5, 1993, and Fokker 
Service Bulletin SBF100-52-055, dated July 20, 1994. The replacement 
shall be done in accordance with Fokker Service Bulletin SBF100-52-
043, dated June 12, 1995. 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 Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, 
Virginia 22314. 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.
    (g) This amendment becomes effective on December 27, 1995.

    Issued in Renton, Washington, on November 27, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-29301 Filed 12-11-95; 8:45 am]
BILLING CODE 4910-13-U