[Federal Register Volume 79, Number 178 (Monday, September 15, 2014)]
[Proposed Rules]
[Pages 54919-54922]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-21916]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0701; Directorate Identifier 2014-CE-025-AD]
RIN 2120-AA64
Airworthiness Directives; Various de Havilland Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Harry E. Williams de Havilland Model DH 82A airplanes, all Cliff
Robertson de Havilland Model DH 82A airplanes, and all de Havilland
Model DH 83 airplanes. This proposed AD was prompted by reports of
structural failure of the attachment of the wing to the fuselage that
resulted from failed lateral fuselage tie rods. This proposed AD would
require inspecting the aircraft maintenance records to determine the
[[Page 54920]]
date of installation or the date of last replacement of the lateral
fuselage tie rods. This proposed AD would also require repetitively
replacing all lateral fuselage tie rods and attaching nuts at a
specified life limit interval. We are proposing this AD to correct the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by October 30,
2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, for de
Havilland DH 82A airplanes, contact de Havilland Support Ltd., Building
213, Duxford Airfield, Cambridge, United Kingdom CB22 4QR, telephone:
+44 (0) 1223 830090; fax: +44 (0) 1223 83008; email:
[email protected], Internet: http://www.dhsupport.com/moth.php.
For service information identified in this proposed AD, for de
Havilland DH 83 airplanes, contact Air Stratus Ltd., Oaksey Park
Airfield, Oaksey, Malmesbury, Wiltshite, United Kingdom SN 16 9SD,
telephone: +44 (0) 1666 575111; no known Internet address.
You may view this referenced service information at the FAA, Small
Airplane Directorate, 901 Locust, Kansas City, Missouri 64016. For
information on the availability of this material at the FAA, call (816)
329-4148.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0701; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: For airplanes covered under Type
Certificate Data Sheet (TCDS) A5PC (Model de Havilland DH 82A airplanes
built in Australia): Andrew McAnaul, Aerospace Engineer, FAA, Fort
Worth Airplane Certification Office, ASW-150 (c/o San Antonio MIDO),
10100 Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210)
308-3365; fax: (210) 308-3370; email: [email protected].
For airplanes covered under TCDS A8EU (Model de Havilland DH 82A
airplanes built in the United Kingdom): Fred Guerin, Aerospace
Engineer, FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Blvd., Suite 100, Lakewood, California 90712; phone (562)
627-5232; fax: (562) 627-5210; email: [email protected].
For airplanes covered under TCDS 2-439 (Model de Havilland DH 83
airplanes built in the United Kingdom): Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; phone: (816) 329-4123; fax: (816) 329-4090;
email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2014-0701;
Directorate Identifier 2014-CE-025-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
During routine maintenance on a de Havilland Model DH 82 airplane,
it was found that the lateral fuselage tie rod at the aft position had
sheared at its location with the spar attachment fitting. Investigation
revealed that the failure was a result of fatigue cracking in the
thread root. In addition, the forward tie rod (which had not fractured)
was distorted and found to have been manufactured from material of
incorrect specification with a lower tensile strength.
During our review of the above-referenced cracking and the related
mandatory service information, we determined that the life limit on the
lateral fuselage tie rods is not currently addressed for airplanes on
the U.S. registry. Mandatory service information is required for
airplanes on the registry in certain other countries, but in the United
States an AD must be issued to require the actions of a service
bulletin for all airplanes.
De Havilland Model DH 82A airplanes (commonly referred to as Tiger
Moths) are type certificated under two type certificates. TCDS A5PC,
currently held by Harry E. Williams, is for airplanes built in
Australia, and TCDS A8EU, currently held by Cliff Robertson, c/o
Gadbois Business Management, is for airplanes built in the United
Kingdom. This type certification approval was not by validation, but by
an acceptance process; as such, the U.S. type certificate holders are
not the manufacturers of the airplanes and the original manufacturers
(de Havilland and its licensees) are not type certificate holders.
De Havilland Support Ltd (DHSL) holds the type certificate
responsibility for de Havilland Model DH 82A airplanes (the type design
for TCDS A8EU) in the United Kingdom.
DHSL is custodian of the airframe design data, manufacturing
drawings, and repair schemes still in existence for de Havilland Model
DH 82A Tiger Moth series airplanes only. In 2012, DHSL entered into a
CAA Type Responsibility Agreement (TRA) so that the airplane remains
eligible, if required, for an ICAO-compliant Certificate of
Airworthiness to facilitate training and pleasure flying.
Similarly, Air Stratus Ltd holds the type certificate
responsibility for de Havilland Model DH 83 airplanes (the type design
for TCDS 2-439) in the United Kingdom.
This condition, if not corrected, could result in structural
failure of the attachment of the wing to the fuselage. We are issuing
this proposed AD to correct the unsafe condition on these products.
Relevant Service Information
We reviewed British Aerospace Military Aircraft and Aerostructures
BAe Aircraft Bulletin for de Havilland Moth Aircraft, Document Type and
Ref No Technical News Sheet CT (Moth) No 29, Issue 3, dated March 1,
1999, which was approved by the Civil Aviation Authority (CAA) for the
United Kingdom to ensure the continued
[[Page 54921]]
airworthiness of these airplanes in the United Kingdom. The service
information introduces a life limit for the lateral fuselage tie rods
and describes procedures for repetitively replacing the lateral
fuselage tie rods and attaching nuts.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 69 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspect the aircraft maintenance 1 work-hour x $85 per Not applicable $85 $5,865
records to determine the date hour = $85
of installation or date of last
replacement of the lateral
fuselage tie rods and attaching
nuts.
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We estimate the following costs to the necessary replacements.
Estimated Costs
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Cost per
Action Labor cost Parts cost product
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Replace lateral fuselage tie rods and 30 work-hours x $85 per hour = $825 $3,375
attaching nuts. $2,550.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This proposed regulation is
within the scope of that authority because it addresses an unsafe
condition that is likely to exist or develop on products identified in
this rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Harry E. Williams, Cliff Robertson, and de Havilland Airplanes:
Docket No. FAA-2014-0701; Directorate Identifier 2019-CE-019-AD.
(a) Comments Due Date
We must receive comments by October 30, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Harry E. Williams and Cliff Robertson Model
de Havilland DH 82A airplanes, all serial numbers, and de Havilland
Model DH 83 airplanes, all serial numbers, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 5341, Fuselage, Wing Attach Fittings.
(e) Unsafe Condition
This AD was prompted by reports of structural failure of the
attachment of the wing to the fuselage that resulted from failed
lateral fuselage tie rods. We are issuing this AD to correct the
unsafe condition on these products.
(f) Compliance
Comply with this AD within the compliance times specified in
paragraphs (g) through (h) of this AD, unless already done.
[[Page 54922]]
(g) Determine Date of Installation or Date of Last Replacement of the
Lateral Fuselage Tie Rods and Attaching Nuts
Within the next 30 days after the effective date of this AD,
review the aircraft records to determine the date of installation or
date of last replacement of the lateral fuselage tie rods and
attaching nuts.
(h) Replace the Lateral Fuselage Tie Rod and Attaching Nuts
Initially replace the lateral fuselage tie rod and attaching
nuts at whichever of the compliance times specified in paragraph
(h)(1) or paragraph (h)(2) of this AD that applies. Repetitively
thereafter replace the lateral fuselage tie rod and attaching nuts
every 2,000 hours TIS or 18 years, whichever occurs first. Do the
replacement following the procedures in paragraph 2.C. of the
Accomplishment Instructions and the table on Figure 1 in British
Aerospace Military Aircraft and Aerostructures BAe Aircraft Bulletin
for De Havilland Moth Aircraft, Document Type and Ref No Technical
News Sheet CT (Moth) No 29, Issue 3, dated March 1, 1999.
(1) If the date of lateral fuselage tie rod installation or date
of last replacement is known: Do the initial replacement at
whichever of the following compliance times in paragraph (h)(1)(i)
or paragraph (h)(1)(ii) of this AD that occurs later:
(i) Upon accumulating 2,000 hours TIS on the lateral fuselage
tie rod or upon reaching 18 years from the last lateral fuselage tie
rod replacement, whichever occurs first; or
(ii) Within the next 6 months after the effective date of this
AD or within the next 100 hours TIS after the effective date of this
AD, whichever occurs first.
(2) If the date of lateral fuselage tie rod installation or date
of last replacement is not known: Do the initial replacement within
the next 6 months after the effective date of this AD or within the
next 100 hours TIS after the effective date of this AD, whichever
occurs first.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager of the Fort Worth Airplane Certification Office
(ACO), the Manager of the Los Angeles Aircraft Certification Office
(ACO), and the Manager of the Standards Office, FAA, have the
authority to approve AMOCs for their respective products covered by
this AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the applicable FAA
office, send it to the attention of the person identified in
paragraphs (j)(1), (j)(2), or (j)(3), as applicable.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(j) Related Information
(1) For more information about this AD for airplanes covered
under Type Certificate Data Sheet (TCDS) A5PC (Model de Havilland DH
82A airplanes built in Australia), contact Andrew McAnaul, Aerospace
Engineer, FAA, Fort Worth ACO, ASW-150 (c/o San Antonio MIDO), 10100
Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210)
308-3365; fax: (210) 308-3370; email: [email protected].
(2) For more information about this AD for airplanes covered
under TCDS A8EU (Model de Havilland DH 82A airplanes built in the
United Kingdom), contact Fred Guerin, Aerospace Engineer, FAA, Los
Angeles ACO, 3960 Paramount Blvd., Suite 100, Lakewood, California
90712; phone (562) 627-5232; fax: (562) 627-5210; email:
[email protected].
(3) For more information about this AD for airplanes covered
under TCDS 2-439 (Model de Havilland DH 83 airplanes built in the
United Kingdom), contact Karl Schletzbaum, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4123; fax: (816) 329-4090;
email: [email protected].
(4) For British Aerospace Military Aircraft and Aerostructures
BAe Aircraft Bulletin for De Havilland Moth Aircraft, Technical New
Sheet CT (Moth) No 29, Issue 3, dated March 1, 1999, service
information identified in this AD, contact:
(i) For de Havilland DH 82A airplanes: de Havilland Support Ltd,
Building 213, Duxford Airfield, Cambridge, United Kingdom CB22 4QR,
telephone: +44 (0) 1223 830090; fax: +44 (0) 1223 83008; email:
[email protected]; Internet: http://www.dhsupport.com/moth.php.
(ii) For de Havilland DH 83 airplanes: Air Stratus Ltd., Oaksey
Park Airfield, Oaksey, Malmesbury, Wiltshite, United Kingdom SN 16
9SD, telephone: +44 (0) 1666 575111; no known Internet address.
(5) You may view this service information at FAA, Small Airplane
Directorate, 901 Locust, Kansas City, Missouri 64016. For
information on the availability of this material at the FAA, call
(816) 329-4148.
Issued in Kansas City, Missouri, on September 8, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014-21916 Filed 9-12-14; 8:45 am]
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