[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]]

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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).

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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

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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