[Federal Register: September 2, 2003 (Volume 68, Number 169)]
[Rules and Regulations]
[Page 52078-52081]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02se03-2]
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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: info@dhsupport.com. 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:
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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32 workhours x $60 per hour = No parts required........ $1,920 $1,920 x 54 = $103,680
$1,920.
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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 bracket
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3 workhours x $60 per hour = $180 per $600 per bracket (2 brackets $180 + 600 = $780
bracket. per airplane).
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We estimate the following costs to accomplish an inspection of the
engine mount frame:
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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16 workhours x $60 per hour = $960 No parts required......... $960 $960 x 54 = $51,840
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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
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Compliance Actions Procedures
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(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.
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(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.
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(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.
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(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.
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(2) Engine Mount Frames
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Actions Compliance Procedures
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(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.
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[[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.
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(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.
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(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: info@dhsupport.com. 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]
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