[Federal Register Volume 68, Number 52 (Tuesday, March 18, 2003)]
[Rules and Regulations]
[Pages 12799-12802]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-6045]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-63-AD; Amendment 39-13081; AD 2003-05-05]
RIN 2120-AA64


Airworthiness Directives; Robert E. Rust Models DeHavilland DH.C1 
Chipmunk 21, 22, and 22A Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Robert E. Rust (R.E. Rust) Models DeHavilland DH.C1 
Chipmunk 21, 22, and 22A airplanes. This AD requires 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 AD decreases 
the safe life limit. This 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 AD are intended to prevent early 
failure of these bushed steel fuselage center-section tie bars, which 
could result in reduced structural

[[Page 12800]]

integrity of the wings. Such a condition could lead to loss of control 
of the airplane.

DATES: This AD becomes effective on April 25, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of April 
25, 2003.

ADDRESSES: You may get the service information 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 
this information at the Federal Aviation Administration (FAA), Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2000-CE-63-AD, 901 Locust, Room 506, Kansas City, Missouri 64106; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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:

Discussion

What Events Have Caused This 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 Is the Potential Impact if FAA Took No Action?

    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.

Has FAA Taken Any Action to This Point?

    We issued a proposal to amend part 39 of the Federal Aviation 
Regulations (14 CFR part 39) to include an AD that would apply to 
certain R.E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on November 15, 2002 (67 FR 
69149). The NPRM proposed to 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, the NPRM proposed to require you to inspect the end lugs to 
determine if bushings are installed in the bolt holes. If bushings are 
present, the NPRM also proposed to reduce the safe life of that part 
from 30,000 fatigue hours to 16, 000 fatigue hours.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:
    --Provide the intent that was proposed in the NPRM for correcting 
the unsafe condition; and
    --do not add any additional burden upon the public than was already 
proposed in the NPRM.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 54 airplanes in the U.S. registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    We estimate the following costs to accomplish the inspection:

----------------------------------------------------------------------------------------------------------------
                                                                      Total cost per      Total cost on U.S.
               Labor cost                        Parts cost              airplane              operators
----------------------------------------------------------------------------------------------------------------
12 workhours x $60 per hour = $720.....  No parts required.........            $720   $720 x 54 = $38,880.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that will be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such replacement:

------------------------------------------------------------------------
                                                      Total cost per
           Labor cost               Parts cost           airplane
------------------------------------------------------------------------
80 workhours x $60 per hour =            $2,250   $4,800 + $2,250 =
 $4,800.                                           $7,050.
------------------------------------------------------------------------

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    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 copy of the final evaluation prepared for this 
action is contained in the Rules Docket. A copy

[[Page 12801]]

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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under 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. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2003-05-05 Robert E. Rust: Amendment 39-13081; 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:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Check the airplane logbook    Upon accumulating   The owner/operator
 to determine if a steel           16,000 fatigue      holding at least
 fuselage center-section tie       hours or within     a private pilot
 bar, part number (P/N)            the next 100        certificate as
 RD.C1.FS.107, is installed.       hours time-in-      authorized by
 Initial steel tie bar fitments    service (TIS)       section 43.7 of
 were done under cover of Repair   after April 25,     the Federal
 Drawings R.C1.FS.191 and          2003 (the           Aviation
 RD.C1.FS.106. Later these         effective date of   Regulations (14
 drawings were included in         this AD),           CFR 43.7) may
 Modification H.288 so fitment     whichever occurs    check the
 may be logged under either.       later.              airplane logbook.
                                                       Calculate fatigue
                                                       hours by
                                                       multiplying the
                                                       TIS by the role
                                                       factor in
                                                       accordance with
                                                       British Aerospace
                                                       Mandatory
                                                       Technical News
                                                       Sheet Series:
                                                       Chipmunk (C1),
                                                       No. 138, Issue:
                                                       5, dated August
                                                       1, 1985.
(2) If, by checking the airplane  Not applicable....  The owner/operator
 logbook, you can positively                           holding at least
 determine that a steel fuselage                       a private pilot
 center-section tie bar, P/N                           certificate as
 RD.C1.FS.107, is not installed.                       authorized by
                                                       section 43.7 of
                                                       the Federal
                                                       Aviation
                                                       Regulations (14
                                                       CFR 43.7) may
                                                       check the
                                                       airplane logbook.
(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
 published life limits of the
 installed tie bar.
(3) If, by checking the airplane  Prior to further    In accordance with
 logbook, you determine that a     flight after the    British Aerospace
 steel fuselage center-section     logbook check       Mandatory
 tie bar, P/N RD.C1.FS.107, is     required in         Technical News
 installed, or cannot positively   paragraph (d)(1)    Sheet Series:
 show that one is not installed.   of this AD.         Chipmunk (C1),
                                                       No. 175, Issue 1,
                                                       dated August 1,
                                                       1985.
(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 records that shows
 compliance with this portion of
 the AD in accordance with
 section 43.9 of the Federal
 Aviation Regulations (14 CFR
 43.9).
(4) The following are the safe    As of April 25,     Not applicable.
 life limit for steel fuselage     2003 (the
 center-section tie bars, P/N      effective date of
 RD.C1.FS.107.                     this AD).
(i) If fitted with bushings in
 the end lug bolt holes: 16,000
 fatigue hours; and.
(ii) If not fitted with bushings
 in the end lug bolt holes:
 30,000 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

[[Page 12802]]

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 
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) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with British Aerospace Mandatory Technical News Sheet Series: 
Chipmunk (C1), No. 138, Issue: 5, dated August 1, 1985, and British 
Aerospace Mandatory Technical News Sheet Series: Chipmunk (C1), No. 
175, Issue 1, dated August 1, 1985. The Director of the Federal 
Register approved this incorporation by reference under 5 U.S.C. 
552(a) and 1 CFR part 51. You may get copies 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 copies at the FAA, 
Central Region, Office of the Regional Counsel, 901 Locust, Room 
506, Kansas City, Missouri, or at the Office of the Federal 
Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on April 25, 2003.

    Issued in Kansas City, Missouri, on March 4, 2003.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-6045 Filed 3-17-03; 8:45 am]
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