[Federal Register Volume 62, Number 243 (Thursday, December 18, 1997)]
[Rules and Regulations]
[Pages 66264-66266]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-32610]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-222-AD; Amendment 39-10248; AD 97-26-05]
RIN 2120-AA64
Airworthiness Directives; British Aerospace (Jetstream) Model HS
748 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 all British Aerospace (Jetstream) Model HS 748 series
airplanes. This action requires inspections of the inspection holes in
all engine `W' frame socket fittings to determine if certain fasteners
have been installed, or if the inspection holes have been reworked; and
corrective action, if necessary. This amendment is prompted by issuance
of mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified in this AD are intended
to prevent fatigue cracking at the inspection hole locations, due to
the installation of certain fasteners or hole enlargement, which could
result in failure of the engine mount structure and consequent
separation of the engine from the airplane.
DATES: Effective January 2, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director
[[Page 66265]]
of the Federal Register as of January 2, 1998.
Comments for inclusion in the Rules Docket must be received on or
before January 20, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-222-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
AI(R) American Support, Inc., 13850 Mclearen Road, Herndon, Virginia
20171. 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: International Branch, ANM-116, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom, notified the FAA
that an unsafe condition may exist on all British Aerospace (Jetstream)
Model HS 748 series airplanes. The CAA advises that drive screws have
been found installed in the inspection holes of engine `W' frame socket
fittings, which resulted in fatigue cracks at the inspection holes. In
addition, investigation revealed that, in some cases, the inspection
holes had been enlarged beyond the original 0.125-inch diameter, which
would reduce the structural strength of the fittings. Such fatigue
cracking at the inspection hole locations, if not detected and
corrected in a timely manner, could result in failure of the engine
mount structure and consequent separation of the engine from the
airplane.
Explanation of Relevant Service Information
British Aerospace (Jetstream) has issued Viscount Preliminary
Technical Leaflet (PTL) No. 501, Issue 2, dated June 1, 1994, including
Appendix 1, dated January 1, 1994, which describes procedures for a
detailed visual inspection of the inspection holes in all engine 'W'
frame socket fittings to determine if drive screws, and/or blind rivets
have been installed, or if the original 0.125-inch diameter hole size
has been reworked. The PTL also describes procedures for reworking the
inspection holes and/or replacement of the 'W' frame fitting, if
necessary. The CAA classified this service information as mandatory and
issued British airworthiness directive 002-09-94, dated September 1994,
in order to assure the continued airworthiness of these airplanes in
the United Kingdom.
FAA's Conclusions
This airplane model is manufactured in the United Kingdom 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 CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the CAA, 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 requires accomplishment of the actions
specified in the PTL described previously, except as described below.
Differences Between This AD and the Service Information
Operators should note that, unlike the procedures described in the
referenced PTL and the British airworthiness directive, this AD will
not permit further flight if drive screws, blind rivets, and/or
reworked holes are found to exist at the inspection hole locations. The
FAA has determined that, due to the safety implications and
consequences associated with the installation of drive screws, blind
rivets, and/or the existence of reworked holes at the inspection hole
locations, corrective action must be accomplished prior to further
flight.
Cost Impact
None of the Jetstream Model HS 748 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 13 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
$780 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-222-AD.'' The postcard will be date stamped and
returned to the commenter.
[[Page 66266]]
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:
97-26-05 British Aerospace Regional Aircraft [Formerly Jetstream
Aircraft Limited, British Aerospace (Commercial Aircraft) Limited]:
Amendment 39-10248. Docket 97-NM-222-AD.
Applicability: All Model HS 748 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
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 (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 prevent fatigue cracking at the inspection hole locations,
due to the installation of drive screws, and/or blind rivets, or
hole enlargement, which could result in failure of the engine mount
structure and consequent separation of the engine from the airplane,
accomplish the following:
(a) Within 12 months after the effective date of this AD,
perform a detailed visual inspection of the inspection holes in all
of the aft engine `W' frame socket fittings to determine if drive
screws and/or blind rivets have been installed, and to determine if
the inspection holes have been reworked, in accordance with PART ONE
of the Accomplishment Instructions of British Aerospace (Jetstream)
Viscount Preliminary Technical Leaflet (PTL) No. 501, Issue 2, dated
June 1, 1994, including Appendix 1, dated January 1, 1994. If a
drive screw or blind rivet is installed, or if any inspection hole
has been reworked, prior to further flight, accomplish follow-on
corrective actions, as applicable, in accordance with PART THREE of
the Accomplishment Instructions of the PTL.
(b) At the next engine `W' frame removal, or within 24 months
after the effective date of this AD, whichever occurs first: Perform
a detailed visual inspection of the inspection holes in all of the
forward engine `W' frame socket fittings to determine if drive
screws and/or blind rivets have been installed, and to determine if
the inspection holes have been reworked, in accordance with PART TWO
of the Accomplishment Instructions of British Aerospace (Jetstream)
Viscount PTL No. 501, Issue 2, dated June 1, 1994, including
Appendix 1, dated January 1, 1994. If a drive screw or blind rivet
is installed, or if any inspection hole has been reworked, prior to
further flight, accomplish follow-on corrective actions, as
applicable, in accordance with PART THREE of the Accomplishment
Instructions of the PTL.
Note 2: Accomplishment of the inspections and/or corrective
actions in accordance with Jetstream Service Bulletin HS748-71-33,
dated September 2, 1994, is considered acceptable for showing
compliance with the requirements of paragraphs (a) and (b) of this
AD.
(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, 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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 British
Aerospace (Jetstream) Viscount Preliminary Technical Leaflet (PTL)
No. 501, Issue 2, dated June 1, 1994, including Appendix 1, dated
January 1, 1994. 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 AI(R) American
Support, Inc., 13850 Mclearen Road, Herndon, Virginia 20171. 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 4: The subject of this AD is addressed in British
airworthiness directive 002-09-94, dated September 1994.
(f) This amendment becomes effective on January 2, 1998.
Issued in Renton, Washington, on December 9, 1997.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-32610 Filed 12-17-97; 8:45 am]
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