[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
