[Federal Register Volume 63, Number 244 (Monday, December 21, 1998)]
[Rules and Regulations]
[Pages 70322-70324]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-33690]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-195-AD; Amendment 39-10958; AD 98-26-15]
RIN 2120-AA64
Airworthiness Directives; British Aerospace (Jetstream) Model
4101 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain British Aerospace (Jetstream) Model 4101
airplanes, that currently requires repetitive detailed visual
inspections to detect cracks in the shear cleats of the roller guide
structural support of the passenger door, and replacement of any
cracked shear cleat with a new shear cleat. That AD also provides for
an optional terminating modification that constitutes
[[Page 70323]]
terminating action for the repetitive inspections. This amendment
mandates accomplishment of the previously optional terminating
modification. This amendment is prompted by reports indicating that
fatigue cracking was detected in the roller guide shear cleats of the
passenger door. The actions specified by this AD are intended to
prevent such fatigue-related cracking, which could result in structural
failure or loss of the passenger door, and consequent rapid
depressurization of the airplane during flight.
DATES: Effective January 25, 1999.
The incorporation by reference of certain publications, as listed
in the regulations, was approved previously by the Director of the
Federal Register as of August 12, 1997 (62 FR 40267, July 28, 1997).
ADDRESSES: 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
Federal Aviation Administration (FAA), Transport Airplane Directorate,
Rules Docket, 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: Norman B. Martenson, Manager,
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 97-16-01,
amendment 39-10090 (62 FR 40267, July 28, 1997), which is applicable to
certain British Aerospace (Jetstream) Model 4101 airplanes, was
published in the Federal Register on October 27, 1998 (63 FR 57266).
The action proposed to require repetitive detailed visual inspections
to detect cracks in the shear cleats of the roller guide structural
support of the passenger door, and replacement of any cracked shear
cleat with a new shear cleat. The action also proposed to mandate
accomplishment of the previously optional terminating modification.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
There are approximately 57 Jetstream Model 4101 airplanes of U.S.
registry that will be affected by this AD.
The inspections that are currently required by AD 97-16-01, and
retained in this AD, take approximately 3 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact of the currently required inspections on
U.S. operators is estimated to be $10,260, or $180 per airplane, per
inspection cycle.
The new modification that is required by this AD will take
approximately 55 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$2,460 per airplane. Based on these figures, the cost impact of the
modification required by this AD on U.S. operators is estimated to be
$328,320, or $5,760 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
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 removing amendment 39-10090 (62 FR
40267, July 28, 1997), and by adding a new airworthiness directive
(AD), amendment 39-10958, to read as follows:
98-26-15 British Aerospace Regional Aircraft [Formerly Jetstream
Aircraft Limited; British Aerospace (Commercial Aircraft) Limited]:
Amendment 39-10958. Docket 97-NM-195-AD. Supersedes AD 97-16-01,
Amendment 39-10090.
Applicability: Jetstream Model 4101 airplanes, constructor's
numbers 41004 through 41099 inclusive; 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 prevent fatigue-related cracking in the shear cleats of the
roller guide structural support of the passenger door, which could
result in structural failure or loss of the passenger door, and
consequent rapid depressurization of the airplane during flight,
accomplish the following:
Restatement of Requirements of AD 97-16-01
(a) Except as provided by paragraph (b) of this AD: Prior to the
accumulation of 6,000 landings, or within 60 days after August 12,
1997 (the effective date of AD 97-16-01, amendment 39-10090),
whichever occurs later, perform a detailed visual inspection to
[[Page 70324]]
detect cracks of the shear cleats of the roller guide structural
support of the passenger door, in accordance with Part 1 of the
Accomplishment Instructions of Jetstream Alert Service Bulletin J41-
A52-043, Revision 2, dated May 6, 1997. Repeat the detailed visual
inspection, as specified in Part 2 of the Accomplishment
Instructions of the alert service bulletin, thereafter at intervals
not to exceed 1,500 landings.
Note 2: Accomplishment of the initial detailed visual inspection
prior to August 12, 1997, in accordance with Jetstream Alert Service
Bulletin J41-52-043, dated March 14, 1997, or Revision 1, dated
April 11, 1997, is considered acceptable for compliance with the
initial inspection required by paragraph (a) of this AD.
(1) If one cracked shear cleat is detected, and the crack is
greater than 0.50 inches, prior to further flight, replace the
cracked shear cleat with a new shear cleat in accordance with the
alert service bulletin.
(2) If one cracked shear cleat is detected, and the crack is
less than or equal to 0.50 inches, within 170 landings following
accomplishment of the inspection required by this paragraph, replace
the cracked shear cleat with a new shear cleat in accordance with
the alert service bulletin.
(3) If more than one cracked shear cleat is detected, but no
single crack is greater than 0.50 inches in length, prior to further
flight, replace all cracked shear cleats with new shear cleats in
accordance with the alert service bulletin.
(b) For airplanes on which all shear cleats have been replaced:
Inspect as required by paragraph (a) of this AD, prior to the
accumulation of 6,000 total landings on the highest time new shear
cleat, or within 60 days after August 12, 1997, whichever occurs
later. Repeat the detailed visual inspection thereafter at intervals
not to exceed 1,500 landings.
New Requirements of This AD
(c) Modify the passenger door (Modification No. JM41576) at all
four roller guide locations in accordance with Jetstream Service
Bulletin J41-52-050, dated May 6, 1997, at the time specified in
paragraph (c)(1) or (c)(2) of this AD, whichever occurs later.
Accomplishment of this modification constitutes terminating action
for the requirements of this AD.
(1) Within 4,000 landings or 2 years after accomplishment of the
initial inspection required by paragraph (a) of this AD. Or
(2) Within 6 months after the effective date of this AD.
(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, 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.
(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 actions shall be done in accordance with Jetstream Alert
Service Bulletin J41-A52-043, Revision 2, dated May 6, 1997, and
Jetstream Service Bulletin J41-52-050, dated May 6, 1997. This
incorporation by reference was approved previously by the Director
of the Federal Register as of August 12, 1997 (62 FR 40267, July 28,
1997). 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.
(g) This amendment becomes effective on January 25, 1999.
Issued in Renton, Washington, on December 15, 1998.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-33690 Filed 12-18-98; 8:45 am]
BILLING CODE 4910-13-U
