Airworthiness Directives; Boeing Model 737-100, -200, and -200C Series Airplanes

[Federal Register Volume 66, Number 239 (Wednesday, December 12, 2001)]
[Rules and Regulations]
[Pages 64099-64100]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-30209]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-221-AD; Amendment 39-12550; AD 2001-24-33]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-100, -200, and -200C 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 737-100, -200, and -200C series 
airplanes, that requires a one-time inspection for damage (i.e., 
chafing) of the power feeder wire bundle for the auxiliary power unit 
(APU) generator and the first officer's elevator down control cable and 
for proper separation between that wire bundle and control cable, and 
corrective action, if necessary. For certain airplanes, this amendment 
also requires attaching the power feeder wire bundle to adjacent wire 
bundles. This action is necessary to prevent a short circuit and 
resultant arcing between the wire bundle and control cable, which could 
sever the control cable. Failure of the first officer's elevator down 
control cable, if combined with a subsequent failure of the captain's 
elevator down control cable, could result in loss of elevator control 
of the airplane. This action is intended to address the identified 
unsafe condition.

DATES: Effective January 16, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 16, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Stephen Oshiro, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 227-2793; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 737-100, -
200, and -200C series airplanes was published in the Federal Register 
on July 23, 2001 (66 FR 38217). That action proposed to require a one-
time inspection for damage (i.e., chafing) of the power feeder wire 
bundle for the auxiliary power unit (APU) generator and the first 
officer's elevator down control cable and for proper separation between 
that wire bundle and control cable, and corrective action, if 
necessary. For certain airplanes, that action also proposed to require 
attaching the power feeder wire bundle to adjacent wire bundles.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 136 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 47 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 1 work 
hour per airplane to accomplish the required inspection, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $2,820, or 
$60 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    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.
    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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the 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

    Accordingly, pursuant to 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

    1. The authority citation for part 39 continues to read as follows:


[[Page 64100]]


    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:

2001-24-33  Boeing: Amendment 39-12550. Docket 2001-NM-221-AD.

    Applicability: Model 737-100, -200, and -200C series airplanes; 
as listed in Boeing Special Attention Service Bulletin 737-24-1144, 
Revision 1, dated June 21, 2001; 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 (b) 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 a short circuit and resultant arcing between the 
power feeder wire bundle for the auxiliary power unit (APU) 
generator and the first officer's elevator down control cable, which 
could sever the control cable, and, if combined with a subsequent 
failure of the captain's elevator down control cable, result in loss 
of elevator control of the airplane, accomplish the following:

Inspection and Corrective Actions

    (a) Within 18 months after the effective date of this AD, 
perform a one-time detailed visual inspection for damage (i.e., 
chafing) of the power feeder wire bundle for the APU generator (wire 
bundle W146) and the first officer's elevator down control cable and 
for proper separation between that control cable and wire bundle, 
and attach wire bundle W146 to adjacent wire bundles, as applicable. 
Do these actions according to Boeing Special Attention Service 
Bulletin 737-24-1144, Revision 1, dated June 21, 2001.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (1) If no damage to the control cable or wire bundle is found, 
and if the distance between the control cable and wire bundle is 
equal to or greater than the minimum separation distance specified 
in the service bulletin: No further action is required.
    (2) If any damage to the first officer's elevator down cable is 
found: Before further flight, replace the elevator down control 
cable with a new cable according to the service bulletin, and do 
paragraph (a)(4) of this AD.
    (3) If any damage to the power feeder wire bundle for the APU 
generator (wire bundle W146) is found: Before further flight, repair 
the wire bundle according to the service bulletin, and do paragraph 
(a)(4) of this AD.
    (4) If the distance between the control cable and wire bundle is 
less than the minimum separation distance specified in the service 
bulletin: Before further flight, reroute the wire bundle by turning 
wire bundle clamps to a position that provides minimum separation 
between the wire bundle and control cable, according to the service 
bulletin.

Alternative Methods of Compliance

    (b) 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, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (c) 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.

Incorporation by Reference

    (d) The actions shall be done in accordance with Boeing Special 
Attention Service Bulletin 737-24-1144, Revision 1, dated June 21, 
2001. This incorporation by reference was approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Boeing Commercial Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on January 16, 2002.

    Issued in Renton, Washington, on November 28, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-30209 Filed 12-11-01; 8:45 am]
BILLING CODE 4910-13-P

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