[Federal Register: November 15, 2002 (Volume 67, Number 221)]
[Proposed Rules]
[Page 69149-69152]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15no02-13]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-CE-63-AD]
RIN 2120-AA64
Airworthiness Directives; Robert E. Rust Models DeHavilland DH.C1
Chipmunk 21, 22, and 22A Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Robert E. Rust (R.E. Rust) Models
DeHavilland
[[Page 69150]]
DH.C1 Chipmunk 21, 22, and 22A airplanes. This proposed AD would
require you to inspect the fuselage to determine if a steel fuselage
center-section tie bar fitted with bushings in the end lug bolt holes
is installed. If this bushed steel fuselage center-section tie bar is
installed, this proposed AD would decrease the safe life limit. This
proposed AD is the result of reports that certain replacement steel
fuselage center-section tie bars installed on the affected airplanes
could fail before the originally published safe life limit. The actions
specified by this proposed AD are intended to prevent early failure of
these bushed steel fuselage center-section tie bars, which could result
in reduced structural integrity of the wings. Such a condition could
lead to loss of control of the airplane.
DATES: The Federal Aviation Administration (FAA) must receive any
comments on this proposed rule on or before January 22, 2003.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2000-CE-63-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. You may view any
comments at this location between 8 a.m. and 4 p.m., Monday through
Friday, except Federal holidays. You may also send comments
electronically to the following address: 9-ACE-7-Docket@faa.gov.
Comments sent electronically must contain ``Docket No. 2000-CE-63-AD''
in the subject line. If you send comments electronically as attached
electronic files, the files must be formatted in Microsoft Word 97 for
Windows or ASCII text.
You may get service information that applies to this proposed AD
from DeHavilland Support Limited, Duxford Airfield, Bldg. 213,
Cambridgeshire, CB2 4QR, United Kingdom, telephone: +44 1223 830090,
facsimile: +44 1223 830085, e-mail: info@dhsupport.com. You may also
view this information at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Cindy Lorenzen, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office, 1895 Phoenix Boulevard,
Suite 450, Atlanta, Georgia; telephone: (770) 703-6078; facsimile:
(770) 703-6097.
SUPPLEMENTARY INFORMATION:
Comments Invited
How Do I Comment on This Proposed AD?
The FAA invites comments on this proposed rule. You may submit
whatever written data, views, or arguments you choose. You need to
include the rule's docket number and submit your comments to the
address specified under the caption ADDRESSES. We will consider all
comments received on or before the closing date. We may amend this
proposed rule in light of comments received. Factual information that
supports your ideas and suggestions is extremely helpful in evaluating
the effectiveness of this proposed AD action and determining whether we
need to take additional rulemaking action.
Are There Any Specific Portions of This Proposed AD I Should Pay
Attention to?
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed rule that
might suggest a need to modify the rule. You may view all comments we
receive before and after the closing date of the rule in the Rules
Docket. We will file a report in the Rules Docket that summarizes each
contact we have with the public that concerns the substantive parts of
this proposed AD.
How Can I Be Sure FAA Receives My Comment?
If you want FAA to acknowledge the receipt of your mailed comments,
you must include a self-addressed, stamped postcard. On the postcard,
write ``Comments to Docket No. 2000-CE-63-AD.'' We will date stamp and
mail the postcard back to you.
Discussion
What Events Have Caused This Proposed AD?
The FAA has received reports that an unsafe condition may exist on
certain R.E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A
airplanes. After a review of several of these airplanes, we have
determined that steel fuselage center-section tie bars, part number
RD.C1.FS.107, are being installed as replacements parts. Some of these
part numbers have been fitted with bushings in the end lugs to cover
scored or oversized holes.
The use of bushings in the end of the lugs on these parts severely
reduces the safe life limit. The original safe life limit established
for the steel fuselage center-section tie bar was 30,000 fatigue hours.
Fatigue hours are hours time-in-service multiplied by the role factor
(operational use).
What Are the Consequences If the Condition Is Not Corrected?
This condition, if not corrected, could result in failure of the
steel fuselage center-section tie bar. Such failure could lead to loss
of control of the airplane.
Is There Service Information That Applies to This Subject?
British Aerospace (now DeHavilland Support Limited) has issued
Mandatory Technical News Sheet No. 175, Issue: 1, dated August 1, 1985
and Mandatory Technical News Sheet No. 138, Issue 5, dated August 1,
1985.
What Are the Provisions of This Service Information?
These Technical News Sheets include procedures for inspecting the
steel fuselage center-section tie bar to determine if the bolt holes in
the lug have bushings and procedures for calculating fatigue hours.
The FAA's Determination and an Explanation of the Provisions of this
Proposed AD
What Has FAA Decided?
After examining the circumstances and reviewing all available
information related to the incidents described above, we have
determined that:
--The unsafe condition referenced in this document exists or could
develop on other R.E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22,
and 22A airplanes of the same type design;
--The actions specified in the previously-referenced service
information should be accomplished on the affected airplanes; and
--AD action should be taken in order to correct this unsafe condition.
What Would This Proposed AD Require?
This proposed AD would require you to check the airplane logbook to
determine if a steel fuselage center-section tie bar, part number
RD.C1.FS.107, is installed on the airplane. If this part number is
installed, this proposed AD would require you to inspect the end lugs
to determine if bushings are installed in the bolt holes. If bushings
are present, this proposed AD would also reduce the safe life of that
part from 30,000 fatigue hours to 16, 000 fatigue hours.
Cost Impact
How Many Airplanes Would This Proposed AD Impact?
We estimate that this proposed AD affects 54 airplanes in the U.S.
registry.
What Would Be the Cost Impact of This Proposed AD on Owners/Operators
of the Affected Airplanes?
We estimate the following costs to accomplish the proposed
inspection:
[[Page 69151]]
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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12 workhours x $60 per hour = $720.. No parts required..... $720 $720 x 54 = $38,880
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We estimate the following costs to accomplish any necessary
replacements that would be required based on the results of the
proposed inspection. We have no way of determining the number of
airplanes that may need such replacement:
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Labor cost Parts cost Total cost per airplane
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80 workhours x $60 per hour = $4,800........ $2,250 $4,800 + $2,250 = $7,050
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Regulatory Impact
Would This Proposed AD Impact Various Entities?
The regulations proposed herein would not have a substantial direct
effect 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, it
is determined that this proposed rule would not have federalism
implications under Executive Order 13132.
Would This Proposed AD Involve a Significant Rule or Regulatory Action?
For the reasons discussed above, I certify that this proposed
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) if
promulgated, 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 copy of the draft regulatory
evaluation prepared for this action has been placed in the Rules
Docket. A copy of it may be obtained by contacting the Rules Docket at
the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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. FAA amends Sec. 39.13 by adding a new airworthiness directive
(AD) to read as follows:
Robert E. Rust: Docket No. 2000-CE-63-AD.
(a) What airplanes are affected by this AD? This AD affects R.E.
Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A airplanes,
serial numbers C1-001 through C1-1014, that are type certificated in
any category.
Note 1: We recommend all owners/operators of DeHavilland DH.C1
Chipmunk 21, 22, and 22A airplanes, serial numbers C1-001 through
C1-1014, with experimental airworthiness certificates comply with
the actions required in this AD.
(b) Who must comply with this AD? Anyone who wishes to operate
any of the airplanes identified in paragraph (a) of this AD must
comply with this AD.
(c) What problem does this AD address? The actions specified by
this AD are intended to prevent failure of the steel fuselage
center-section tie bar prior to the originally published safe life,
which could result in reduced structural integrity of the wings.
Such a condition could lead to loss of control of the airplane.
Steel fuselage center-section tie bars fitted with bushings in the
end lug bolt holes have a reduced safe life of 16,000 fatigue hours.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Check the airplane logbook to Upon accumulating 16,000 The owner/operator holding at least a
determine if a steel fuselage center- fatigue hours or within private pilot certificate as authorized
section tie bar, part number (P/N) the next 100 hours time- by section 43.7 of the Federal Aviation
RD.C1.FS.107, is installed. Initial in-service (TIS) after Regulations (14 CFR 43.7) may check the
steel tie bar fitments were done under the effective date of airplane logbook. Calculate fatigue
cover of Repair Drawings R.C1.FS.191 and this AD, whichever occurs hours by multiplying the TIS by the role
RD.C1.FS.106. Later these drawings were later. factor in accordance with British
included in Modification H.288 so Aerospace Mandatory Technical News Sheet
fitment may be logged under either. Series: Chipmunk (C1), No. 138, Issue:
5, dated August 1, 1985.
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(2) If, by checking the airplane logbook,
you can positively determine that a
steel fuselage center-section tie bar, P/
N RD.C1.FS.107, is not installed:
(i) you must make an entry into the
aircraft records that shows
compliance with paragraphs (d)(1)
and (d)(2) of this AD in accordance
with section 43.9 of the Federal
Aviation Regulations (14 CFR 43.9);
and
(ii) continue to comply with the Not applicable............ The owner/operator holding at least a
published life limits of the private pilot certificate as authorized
installed tie bar. by section 43.7 of the Federal Aviation
Regulations (14 CFR 43.7) may check the
airplane logbook.
[[Page 69152]]
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(3) If, by checking the airplane logbook,
you determine that a steel fuselage
center-section tie bar, P/N
RD.C1.FS.107, is installed, or cannot
positively show that one is not
installed:
(i) inspect the lug bolt holes to
determine if bushings have been
installed;
(ii) if bushings have been installed,
the safe life limit for that part is
now 16,000 fatigue hours;
(iii) if bushing have not been
installed, the safe life limit for
that part remains at 30,000 fatigue
hours; and
(iv) make an entry into the aircraft Prior to further flight In accordance with British Aerospace
records that shows compliance with after the logbook check Mandatory Technical News Sheet No. 175,
this portion of the AD in accordance required in paragraph Issue 1, dated August 1, 1985.
with section 43.9 of the Federal (d)(1) of this AD.
Aviation Regulations (14 CFR 43.9).
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(4) The following are the safe life limit
for steel fuselage center-section tie
bars, P/N RD.C1.FS.107:
(i) If fitted with bushings in the
end lug bolt holes: 16,000 fatigue
hours; and
(ii) If not fitted with bushings in As of the effective date Not applicable.
the end lug bolt holes: 30,000 of this AD.
fatigue hours.
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(e) Can I comply with this AD in any other way? You may use an
alternative method of compliance or adjust the compliance time if:
(1) Your alternative method of compliance provides an equivalent
level of safety; and
(2) The Manager, Atlanta Aircraft Certification Office (ACO),
approves your alternative. Submit your request through an FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Atlanta ACO.
Note: This AD applies to each airplane identified in paragraph
(a) of this AD, 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 (e) 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 you have not eliminated the unsafe condition, specific
actions you propose to address it.
(f) Where can I get information about any already-approved
alternative methods of compliance? Contact Cindy Lorenzen, Aerospace
Engineer, FAA, Atlanta Aircraft Certification Office, 1895 Phoenix
Boulevard, Suite 450, Atlanta, Georgia; telephone: (770) 703-6078;
facsimile: (770) 703-6097.
(g) What if I need to fly the airplane to another location to
comply with this AD? The FAA can issue a special flight permit under
Sec. Sec. sections 21.197 and 21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a
location where you can accomplish the requirements of this AD.
(h) How do I get copies of the documents referenced in this AD?
You may get copies of the documents referenced in this AD from
DeHavilland Support Limited, Duxford Airfield, Bldg. 213,
Cambridgeshire, CB2 4QR, United Kingdom, telephone: +44 1223 830090,
facsimile: +44 1223 830085, e-mail: info@dhsupport.com. You may view
these documents at FAA, Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.
Issued in Kansas City, Missouri, on November 6, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-28999 Filed 11-14-02; 8:45 am]
BILLING CODE 4910-13-P