[Federal Register Volume 67, Number 221 (Friday, November 15, 2002)]
[Proposed Rules]
[Pages 69149-69152]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-28999]


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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: [email protected]. 
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: [email protected]. 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
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
(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.
------------------------------------------
(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]]

 
------------------------------------------
(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).
------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------

    (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: [email protected]. 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