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

[Federal Register Volume 68, Number 169 (Tuesday, September 2, 2003)]
[Rules and Regulations]
[Pages 52078-52081]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-21742]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-64-AD; Amendment 39-13291; AD 2003-17-16]
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 
repetitively inspect the tailplane attachment brackets and replace each 
bracket at a specified time. This AD also requires you to repetitively 
inspect each joint of the port and starboard engine mount frame and the 
rear upper mount frame tubes for cracks and/or damage and repair any 
cracks and/or damage found. This AD is the result of reports of stress 
corrosion cracking found on the tailplane attachment brackets and 
fatigue cracking and chaffing of the engine mount frame. The actions 
specified by this AD are intended to prevent failure of the tailplane 
attachment brackets caused by stress corrosion cracking and failure of 
the engine mount, which could result in loss of the tail section and 
separation of the engine from the airplane respectively. Such failures 
could lead to loss of control of the airplane.

DATES: This AD becomes effective on October 10, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
October 10, 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-64-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?

    We received reports that an unsafe condition exists on certain R.E. 
Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A airplanes. After 
reviewing several of these airplanes, stress corrosion cracking was 
found on the tailplane attachment brackets and fatigue cracks and 
chaffing were found on the engine mount frame.
    Cracks in the engine mount frame were found in the area of the 
junction of the front and rear top tube and engine mounting foot 
support brackets and in the front of the frame. We have determined that 
fatigue is the cause of the cracks. The upper aft mount frame tubes 
were also found to have damage caused by chaffing by the cowling 
support rod.

What Is the Potential Impact if FAA Took No Action?

    These conditions, if not corrected, could result in failure of the 
tailplane attachment brackets and failure of the engine mount. Such 
failures 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 
supplemental notice of proposed rulemaking (NPRM) on April 15, 2003 (68 
FR 18571). The supplemental NPRM proposed to require you to 
repetitively inspect the tailplane attachment brackets and replace each 
bracket at a specified time. The NPRM also proposed to require you to 
repetitively inspect each joint of the port and starboard engine mount 
frame and the

[[Page 52079]]

rear upper mount frame tubes for cracks and/or damage and repair any 
cracks and/or damage found.

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 supplemental NPRM for 
correcting the unsafe condition; and
    --Do not add any additional burden upon the public than was already 
proposed in the Supplemental NPRM.

How Does the Revision to 14 CFR Part 39 Affect This AD?

    On July 10, 2002, FAA published a new version of 14 CFR part 39 (67 
FR 47997, July 22, 2002), which governs FAA's AD system. This 
regulation now includes material that relates to special flight 
permits, alternative methods of compliance, and altered products. This 
material previously was included in each individual AD. Since this 
material is included in 14 CFR part 39, we will not include it in 
future AD actions.

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 an inspection of the 
tailplane attachment brackets:

 
----------------------------------------------------------------------------------------------------------------
                                                               Total cost per
            Labor cost                     Parts cost             airplane       Total cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
32 workhours x $60 per hour =      No parts required........          $1,920   $1,920 x 54 = $103,680
 $1,920.
----------------------------------------------------------------------------------------------------------------

    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:

----------------------------------------------------------------------------------------------------------------
               Labor cost                            Parts cost                    Total cost per bracket
----------------------------------------------------------------------------------------------------------------
3 workhours x $60 per hour = $180 per     $600 per bracket (2 brackets     $180 + 600 = $780
 bracket.                                  per airplane).
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish an inspection of the 
engine mount frame:

----------------------------------------------------------------------------------------------------------------
                                                                 Total cost per
            Labor cost                      Parts cost              airplane      Total cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
16 workhours x $60 per hour = $960  No parts required.........            $960   $960 x 54 = $51,840
----------------------------------------------------------------------------------------------------------------

    The FAA has no method of determining the number of repairs or 
replacements each owner/operator will incur over the life of each of 
the affected airplanes based on the results of the proposed 
inspections. We have no way of determining the number of airplanes that 
may need such repair. The extent of damage may vary of each airplane.

Compliance Time of This AD

What Will Be the Compliance Time of This AD?

    The compliance time for the initial inspections in this AD is 
``within the next 90 days after the effective date of this AD.''

Why Is the Compliance Time Presented in Calendar Time Instead of Hours 
Time-in-Service (TIS)?

    An unsafe condition specified by this AD is caused by corrosion. 
Corrosion can occur regardless of whether the aircraft is in operation 
or is in storage. Therefore, to assure that the unsafe condition 
specified in this AD does not go undetected for a long period of time, 
the compliance is presented in calendar time instead of TIS.

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 of it may be obtained 
by contacting the

[[Page 52080]]

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

0
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

0
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]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2003-17-16 Robert E. Rust: Amendment 39-13291; Docket No. 2000-CE-
64-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 tailplane attachment 
brackets caused by stress corrosion cracking and failure of the 
engine mount, which could result in loss of the tail section and 
separation of the engine from the airplane respectively. Such 
failures could lead to loss of control of the airplane.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

                                        (1) Tailplane Attachment Brackets
----------------------------------------------------------------------------------------------------------------
                Compliance                                  Actions                           Procedures
----------------------------------------------------------------------------------------------------------------
(i) Initially inspect within the next 90   Inspect, using dye penetrant, the         In accordance with British
 days after October 10, 2003 (the date of   tailplane attachment brackets, part-      Aerospace Military
 this AD).                                  number (P/N) C1.TP.167 (or FAA-approved   Aircraft and
(A) Inspect thereafter at intervals not     equivalent part) for cracks.              Aerostructures (BAe
 to exceed 6 months or 150 fatigue hours,                                             Aircraft) Mandatory
 whichever occurs first, until the                                                    Technical News Sheet CT
 modification required by paragraph                                                   (C1) No. 176, Issue 2,
 (d)(1)(ii) of this AD is incorporated.                                               dated November 1, 1997;
(B) When the modification required by                                                 and Civil Modification
 paragraph (d)(1)(ii) is incorporated,                                                Mandatory Modification No.
 you may terminate the repetitive                                                     Chipmunk H357, dated March
 inspections of the tailplane attachment                                              12, 1984. Calculate
 brackets.                                                                            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.
------------------------------------------
(ii) At whichever of the following that    Replace the tailplane attachment bracket  In accordance with British
 occurs first:                              by incorporating Modification H357 (P/N   Aerospace Military
(A) Prior to further flight after the       C1.TP.313) or FAA-approved equivalent     Aircraft and
 inspection where any crack is found; or    part number. Installing P/N C1.TP.313     Aerostructures (BAe
(B) Upon accumulating 9,984 fatigue hours   )or FAA-approved equivalent part          Aircraft) Mandatory
 or within the next 90 days after October   number) terminates the repetitive         Technical News Sheet CT
 10, 2003 (the effective date of this       inspection requirement of the tailplane   (C1) No. 176, Issue 2,
 AD), whichever occurs later.               attachment brackets.                      dated November 1, 1997;
                                                                                      and Civil Modification No.
                                                                                      Chipmunk H357, dated March
                                                                                      12, 1984. Calculate
                                                                                      fatigue hours by
                                                                                      multiplying the TIS by the
                                                                                      role in accordance with
                                                                                      British Aerospace
                                                                                      Mandatory Technical News
                                                                                      Sheet Series: Chipmunk
                                                                                      (C1), No. 138, Issue: 5,
                                                                                      dated August 1, 1985.
------------------------------------------
(iii) As of October 10, 2003 (the          Only install a tailplane attachment       Not applicable.
 effective date of this AD).                bracket that is P/N C1.TP.313. or FAA-
                                            approved equivalent part number.
------------------------------------------
(iv) As of October 10, 2003 (the           Incorporate the following into the        In accordance with British
 effective date of this AD).                Aircraft Logbook: ``In accordance with    Aerospace Military
                                            AD 2003-17-16, the tailplane attachment   Aircraft and
                                            bracket is life limited to 9,984          Aerostructures (BAe
                                            fatigue hours.''                          Aircraft) Mandatory
                                                                                      Technical News Sheet CT
                                                                                      (C1) No. 176, Issue 2,
                                                                                      dated November 1, 1997.
----------------------------------------------------------------------------------------------------------------


                                             (2) Engine Mount Frames
----------------------------------------------------------------------------------------------------------------
                 Actions                                  Compliance                          Procedures
----------------------------------------------------------------------------------------------------------------
(i) Inspect each joint of the port and     Initially inspect within the next 90      In accordance with British
 starboard engine mount and the rear        days after October 10, 2003 (the          Aerospace Aerostructures
 upper mount frame tubes for cracks and     effective date of this AD).               Limited (BAe Aircraft)
 damage.                                    Repetitively inspect thereafter at        Mandatory Technical News
                                            intervals not to exceed 600 hours TIS.    Sheet CT (C1) No. 190,
                                                                                      Issue 2, dated April 1,
                                                                                      1995.
------------------------------------------

[[Page 52081]]

 
(ii) If cracks or damage is found during   Prior to further flight after the         Repair in accordance with
 any inspection required in paragraph       inspection in which any crack or damage   AC 43.13-1B, Change 1,
 (d)(2)(i) of this AD:                      is found. Repetitively inspect as         dated September 27, 2001,
(A) obtain a repair scheme from the         required in paragraph (d)(2)(i) of this   Chapter 4, Paragraph 4-99
 manufacturer through the FAA at the        AD.                                       or in accordance with the
 address specified in paragraph (e) of                                                repair scheme obtained
 this AD and incorporate this repair                                                  from DeHavilland Support
 scheme, or repair in accordance with FAA                                             Limited, Duxford Airfield,
 Advisory Circular (AC) 43.13-1B, Change                                              Bldg. 213, Cambridgeshire,
 1, dated September 27, 2001, Chapter 4,                                              CB2 4QR, United Kingdom.
 Paragraph 4-99; or                                                                   Obtain this repair scheme
(B) replace with a new or serviceable                                                 through the FAA at the
 part.                                                                                address specified in
                                                                                      paragraph (f) of this AD.
                                                                                      Replace in accordance with
                                                                                      British Aerospace
                                                                                      Aerostructures Limited
                                                                                      (BAe Aircraft) Mandatory
                                                                                      Technical News Sheet CT
                                                                                      (C1) No. 190, Issue 2,
                                                                                      dated April 1, 1995, or AC
                                                                                      43.13-1B, Change 1, dated
                                                                                      September 27, 2001,
                                                                                      Chapter 4, Paragraph 4-99.
------------------------------------------
(iii) Bind the rear upper mount frame      Prior to further flight after any         In accordance with British
 tubes with a high density polythene tape   inspection required in paragraph          Aerospace Aerostructures
 at the location where the cowling          (d)(2)(i) of this AD if no cracks or      Limited (BAe Aircraft)
 support rod clip is secured.               damage is found, and prior to further     Mandatory Technical News
                                            flight after any repairs or replacement   Sheet CT (C1) No. 190,
                                            is made as required in paragraph          Issue 2, dated April 1,
                                            (d)(2)(ii) of this AD .                   1995.
----------------------------------------------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? To use an 
alternative method of compliance or adjust the compliance time, use 
the procedures in 14 CFR 39.19. Send these requests to the Manager, 
Atlanta Aircraft Certification Office (ACO). 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.
    (f) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with British Aerospace Military Aircraft and Aerostructures (BAe 
Aircraft) Mandatory Technical News Sheet CT (C1) No. 176, Issue 2, 
dated November 1, 1997; Civil Modification Mandatory Modification 
No. Chipmunk H357, dated March 12, 1984; British Aerospace Mandatory 
Technical News Sheet Series: Chipmunk (C1), No. 138, Issue: 5, dated 
August 1, 1985; and British Aerospace Aerostructures Limited (BAe 
Aircraft) Mandatory Technical News Sheet CT (C1) No. 190, Issue 2, 
including Appendix 1 (Part B), dated April 1, 1995. 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.
    (g) When does this amendment become effective? This amendment 
becomes effective on October 10, 2003.

    Issued in Kansas City, Missouri, on August 19, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-21742 Filed 8-29-03; 8:45 am]
BILLING CODE 4910-13-P

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