[Federal Register Volume 63, Number 131 (Thursday, July 9, 1998)]
[Proposed Rules]
[Pages 37083-37085]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-18155]
[[Page 37083]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-141-AD]
RIN 2120-AA64
Airworthiness Directives; Construcciones Aeronauticas, S.A.
(CASA) Model C-212 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all CASA Model C-212 series
airplanes. This proposal would require repetitive visual inspections
for damage or ``electrical spark marks'' on the cover plates for the
fuel pumps, and corrective actions, if necessary. This proposal also
would require modification of the fuel pump installation by
incorporating a non-conductive film on the cover plate, which would
constitute terminating action for this AD. This proposal is prompted by
issuance of mandatory continuing airworthiness information by a foreign
civil airworthiness authority. The actions specified by the proposed AD
are intended to prevent electrical shorting between the fuel pump
electrical connections and the fuel pump cover plate, which could
result in the ignition of fuel vapor, and consequent fuel tank
explosion/fire.
DATES: Comments must be received by August 10, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-141-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain.
This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-141-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-141-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direccion General de Aviacion (DGAC), which is the
airworthiness authority for Spain, notified the FAA that an unsafe
condition may exist on all CASA Model C-212 series airplanes. The DGAC
advises that an operator of this airplane model discovered ``electrical
spark marks'' on several fuel pump cover plates, which indicated that
electrical shorting was occurring. The main fuel pump cover plates had
sustained the most damage, while the auxiliary fuel pump cover plates
were only slightly damaged. The most severe damage involved the
discoloration and deformation of the outer surface of the cover plate.
Additionally, the isolated bushing for the positive screw was damaged,
and ``electrical spark marks'' were also found between the positive
screw and the fuel pump cartridge surface. Since other airplanes of
this type design that are equipped with this particular pump and cover
may be subject to such damage, an inspection of the affected area is
warranted. Such electrical shorting between the fuel pump electrical
connections and the fuel pump cover plate, if not corrected, could
result in the ignition of fuel vapor, and consequent fuel tank
explosion/fire.
Explanation of Relevant Service Information
The manufacturer has issued CASA Maintenance Instructions COM 212-
252, Revision 0, dated July 15, 1996. This document describes
procedures for repetitive visual inspections for damage or ``electrical
spark marks'' on the cover plates for the fuel pumps, and corrective
actions, if necessary. The corrective actions include inspections for
overheating of wires, and for additional ``electrical spark marks''
between the positive screw terminal and the surrounding cartridge or
pump face body; and modification of the cover plate to incorporate a
non-conductive film. Such modification would eliminate the need for the
repetitive inspections described previously. Accomplishment of the
actions specified in the maintenance instructions is intended to
adequately address the identified unsafe condition. The DGAC classified
these maintenance instructions as mandatory and issued Spanish
airworthiness directive 10/96, dated November 5, 1996, in order to
assure the continued airworthiness of these airplanes in Spain.
FAA's Conclusions
This airplane model is manufactured in Spain and is type
certificated for operation in the United States under the provisions of
Section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified
[[Page 37084]]
in the maintenance instructions described previously, except as
discussed below.
Differences Between Proposed Rule and Foreign AD
The proposed AD would differ from the parallel Spanish
airworthiness directive in that the proposed AD would require the
accomplishment of the terminating action for the repetitive
inspections. The Spanish airworthiness directive provides for that
action as optional.
Mandating the terminating action is based on the FAA's
determination that long-term continued operational safety will be
better assured by modifications or design changes to remove the source
of the problem, rather than by repetitive inspections. The ``electrical
spark marks,'' which are the subject of the inspection required by the
proposed AD, are indicative of previous electrical shorting, which in
itself represents an immediate hazard because of the close proximity of
fuel. Because the inspection technique does not allow detection of a
discrepancy prior to the existence of an unsafe condition, repetitive
inspections are not considered adequate for long-term continued
operational safety.
Cost Impact
The FAA estimates that 38 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 1 work hour per airplane to accomplish
the proposed inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection proposed by
this AD on U.S. operators is estimated to be $2,280, or $60 per
airplane.
It would take approximately 5 work hours per airplane to accomplish
the proposed modification, at an average labor rate of $60 per work
hour. The cost of required parts would be minimal. Based on these
figures, the cost impact of the modification proposed by this AD on
U.S. operators is estimated to be $11,400, or $300 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed requirements
of this AD action, and that no operator would accomplish those actions
in the future if this AD were not adopted.
Regulatory Impact
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that 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); 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 is contained 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, pursuant to 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. Section 39.13 is amended by adding the following new
airworthiness directive:
Construcciones Aeronauticas, S.A. (CASA): Docket 98-NM-141-AD.
Applicability: All Model C-212 series airplanes, certificated in
any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, 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 (c) 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 the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent electrical shorting between the fuel pump electrical
connections and the fuel pump cover plate, which could result in the
ignition of fuel vapor, and consequent fuel tank explosion/fire,
accomplish the following:
(a) Within 100 flight hours after the effective date of this AD,
perform a visual inspection for damage or ``electrical spark marks''
on the cover plates for the fuel pumps, in accordance with CASA
Maintenance Instructions COM 212-252, Revision 0, dated July 15,
1996.
(1) If no damage or ``electrical spark mark'' is detected,
repeat the visual inspection thereafter at intervals not to exceed
300 flight hours until the terminating action identified in
paragraph (b) of this AD is accomplished.
(2) If any damage or ``electrical spark mark'' is detected on
the cover plate, prior to further flight, inspect the wires for
overheating damage and the positive screw terminal of the fuel pump
for ``electrical spark marks'' between the positive screw terminal
and the surrounding cartridge or the pump body face; replace any
damaged wire with a new or serviceable wire, and accomplish
paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable, in
accordance with the maintenance instructions.
(i) If no ``electrical spark mark'' is detected between the
positive screw terminal and the surrounding cartridge or pump body
face, prior to further flight, modify the fuel pump installation by
incorporating a non-conductive film on the cover plate.
Accomplishment of this modification constitutes terminating action
for the requirements of this AD.
(ii) If any ``electrical spark mark'' is detected between the
positive screw terminal and the surrounding cartridge or the pump
body face, prior to further flight, modify the fuel pump
installation by installing a new fuel pump and incorporating a non-
conductive film on the cover plate. Accomplishment of this
modification constitutes terminating action for the requirements of
this AD.
(b) Within 12 months after the effective date of this AD,
inspect the wires for overheating damage and the positive screw
terminal of the fuel pump for ``electrical spark marks'' between the
positive screw terminal and the surrounding cartridge or the pump
body face; replace any damaged wire with a new or serviceable wire,
and accomplish paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as
applicable, in accordance with CASA Maintenance Instructions COM
212-252, Revision 0, dated July 15, 1996, even if no damage or
``electrical spark mark'' has been detected on the cover plate.
Accomplishment of this modification constitutes terminating action
for the requirements of this AD.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance
[[Page 37085]]
Inspector, who may add comments and then send it to the Manager,
International Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
Note 3: The subject of this AD is addressed in Spanish
airworthiness directive 10/96, dated November 5, 1996.
Issued in Renton, Washington, on July 1, 1998.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-18155 Filed 7-8-98; 8:45 am]
BILLING CODE 4910-13-U
