[Federal Register Volume 66, Number 219 (Tuesday, November 13, 2001)]
[Rules and Regulations]
[Pages 56753-56755]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-28023]



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 Rules and Regulations
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  Federal Register / Vol. 66, No. 219 / Tuesday, November 13, 2001 / 
Rules and Regulations  

[[Page 56753]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-260-AD; Amendment 39-12496; AD 2001-22-17]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9-81, -9-82, 
-9-83, and -9-87 Series Airplanes; Model MD-88 Airplanes; and Model MD-
90-30 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 McDonnell Douglas Model DC-9-81, -9-82, -9-83, 
and -9-87 series airplanes; Model MD-88 airplanes; and Model MD-90-30 
series airplanes. This action requires repetitive inspections of the 
electric motors (or motors) of the auxiliary hydraulic pump for 
electrical resistance, continuity, mechanical rotation, and associated 
wiring resistance/voltage; and corrective actions, if necessary. The 
actions specified by this AD are intended to prevent various failures 
of the electric motor(s) of the auxiliary hydraulic pump and associated 
wiring, which could result in fire at the auxiliary hydraulic pump and 
consequent damage to the adjacent electrical equipment and/or 
structure. This action is intended to address the identified unsafe 
condition.

DATES: Effective December 18, 2001.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD80-29A067, dated October 21, 1999; and McDonnell Douglas 
Alert Service Bulletin MD90-29A018, dated October 21, 1999; as listed 
in the regulations, is approved by the Director of the Federal Register 
as of December 18, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024). 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 FAA, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Albert Lam, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (526) 627-5346; fax (562) 627-5210.

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 McDonnell Douglas Model 
DC-9-81, -9-82, -9-83, and -9-87 series airplanes; Model MD-88 
airplanes; and Model MD-90-30 series airplanes; was published in the 
Federal Register on December 6, 2000 (65 FR 76185). That action 
proposed to require repetitive inspections of the number 1 and 2 
electric motors of the auxiliary hydraulic pump for electrical 
resistance, continuity, mechanical rotation, and associated wiring 
resistance/voltage; and corrective actions, if necessary.

Other Relevant Rulemaking

    This AD affects McDonnell Douglas Model DC-9-81, -9-82, -9-83, and 
-9-87 series airplanes (i.e., MD-80 series airplanes); Model MD-88 
airplanes; and Model MD-90-30 series airplanes. The FAA is planning to 
issue a separate AD for McDonnell Douglas Model DC-10 series airplanes, 
Model MD-10 series airplanes, and Model MD-11 series airplanes, to 
address the identified unsafe condition.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Correct Number of Motors Specified

    Two operators indicate that, on the affected twin-jet airplanes, 
there is only one electric motor on an auxiliary hydraulic pump. The 
language in the final rule has been corrected accordingly.

Request To Extend the Interval for Repetitive Inspection

    An operator recommends that the repetitive interval for inspection 
of the electric motor(s) on an auxiliary hydraulic pump be extended 
from 5,000 flight hours to 5,600 flight hours, so that the inspection 
can be done during scheduled maintenance checks. The FAA concurs with 
the commenter's request to extend the compliance time for the 
repetitive inspections. Extending the compliance time by 600 flight 
hours will not adversely affect safety, and will allow the inspection 
to be performed at a base during regularly scheduled maintenance where 
special equipment and trained maintenance personnel will be available 
if necessary. Paragraphs (b), (c), and (d) of the final rule have been 
revised to specify an interval for repetitive inspection of 5,600 
flight hours.

Request To Change the Inspection Method

    The same operator indicates that the inspection method specified in 
the service bulletin could damage a serviceable electric motor in an 
auxiliary hydraulic pump. The operator suggests that the applicable 
Boeing service bulletin be revised to specify a friction check 
procedure that poses less risk of damage to the electric motor. While 
agreeing that the test in question could be improved, the FAA finds the 
test acceptable for the required inspection. Therefore, no change has 
been made to the final rule in this regard.

Request To Change Time of Initial Inspection for Certain Operators

    Another operator indicates that some operators have already 
performed

[[Page 56754]]

inspections of the electric motor(s) of an auxiliary hydraulic pump and 
its associated wiring, in accordance with the service bulletin. For 
these operators, the compliance period for the initial inspection 
should be one repetitive interval since the last inspection, rather 
than within 12 months after the effective date of the AD. The FAA 
concurs and has revised paragraph (a) of the final rule to add a new 
paragraph (a)(3) that provides a compliance time for the initial 
inspection for those operators which have already performed that 
inspection.

Request To Separate Requirements for Inspection of the Motor(s) and 
the Wiring

    Finally, an operator suggests that inspection of the electric 
motor(s) on an auxiliary hydraulic pump and inspection of the 
associated wiring be addressed in separate paragraphs, so that the two 
inspections may be tracked individually. The operator points out that 
the electric motors may be removed from one pump to another and that 
the auxiliary hydraulic pumps may be moved from one airplane to 
another. Separate tracking of the required inspections decreases the 
risk of inadvertent non-compliance. The FAA does not concur with the 
commenter's suggestion. The auxiliary hydraulic pump is part of the 
airplane system that needs to be inspected along with its associated 
wiring. If a pump were to be removed and installed on another airplane, 
that pump would need to be re-inspected along with the associated 
wiring on that airplane. Therefore, no change to the final rule is 
necessary in this regard.

Cost Impact

    There are approximately 1,292 Model DC-9-81, -9-82, -9-83, and -9-
87 series airplanes; Model MD-88 airplanes; and Model MD-90-series 
airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 697 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 $41,820 or $60 per airplane, per 
inspection cycle.
    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:

    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:

2001-22-17 McDonnell Douglas:
    Amendment 39-12496. Docket 2000-NM-260-AD.

    Applicability: Model DC-9-81, -9-82, -9-83, and ``9-87 series 
airplanes, and Model MD-88 airplanes, as listed in McDonnell Douglas 
Alert Service Bulletin MD80-29A067, dated October 21, 1999; and 
Model MD-90-30 series airplanes, as listed in McDonnell Douglas 
Alert Service Bulletin MD90-29A018, dated October 21, 1999; 
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 (e) 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 various failures of electric motors of the auxiliary 
hydraulic pump and associated wiring, which could result in fire at 
the auxiliary hydraulic pump and consequent damage to the adjacent 
electrical equipment and/or structure, accomplish the following:

Inspection

    (a) Do a detailed inspection of the electric motor(s) of the 
auxiliary hydraulic pump for electrical resistance, continuity, 
mechanical rotation, and associated wiring resistance/voltage, per 
McDonnell Douglas Alert Service Bulletin MD80-29A067, dated October 
21, 1999 (for Model DC-9-81, -9-82, -9-83, and ``9-87 series 
airplanes, and Model MD-88 airplanes); or McDonnell Douglas Alert 
Service Bulletin MD90-29A018, dated October 21, 1999 (for Model MD-
90-30 series airplanes); as applicable; at the applicable time 
specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD.
    (1) For airplanes that have accumulated 3,000 total flight hours 
or more as of the effective date of this AD: Inspect within 12 
months after the effective date of this AD.
    (2) For airplanes that have accumulated less than 3,000 total 
flight hours as of the effective date of this AD: Inspect within 12 
months after accumulating 3,000 total flight hours.
    (3) For airplanes on which the inspection has been accomplished 
prior to the effective date of this AD: Inspect within 12 months 
after the effective date of this AD or within 5,600 flight hours 
after the previous inspection, whichever occurs later.

Condition 1, No Failures: Repetitive Inspections

    (b) If no failures are detected during the inspection required 
by paragraph (a) of this AD, repeat the inspection required by 
paragraph (a) of this AD every 5,600 flight hours.

Condition 2, Failure of Any Pump Motor: Replacement and Repetitive 
Inspections

    (c) If any pump motor fails during any inspection required by 
paragraph (a) of this AD, before further flight, replace the failed

[[Page 56755]]

auxiliary hydraulic pump with a serviceable pump, per McDonnell 
Douglas Alert Service Bulletin MD80-29A067, dated October 21, 1999 
(for Model DC-9-81, -9-82, -9-83, and ``9-87 series airplanes, and 
Model MD-88 airplanes); or McDonnell Douglas Alert Service Bulletin 
MD90-29A018, dated October 21, 1999 (for Model MD-90-30 series 
airplanes); as applicable. Repeat the inspection required by 
paragraph (a) of this AD every 5,600 flight hours.

Condition 3, Failure of Any Wiring: Repair and Repetitive Inspection

    (d) If any wiring fails during any inspection required by 
paragraph (a) of this AD, before further flight, troubleshoot and 
repair the failed wiring, per McDonnell Douglas Alert Service 
Bulletin MD80-29A067, dated October 21, 1999 (for Model DC-9-81, -9-
82, -9-83, and ``9-87 series airplanes, and Model MD-88 airplanes); 
or McDonnell Douglas Alert Service Bulletin MD90-29A018, dated 
October 21, 1999 (for Model MD-90-30 series airplanes); as 
applicable. Repeat the inspection required by paragraph (a) of this 
AD every 5,600 flight hours.

Alternative Methods of Compliance

    (e) 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, Los Angeles 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, Los Angeles ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permit

    (f) 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

    (g) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin MD80-29A067, dated October 21, 1999; 
and McDonnell Douglas Alert Service Bulletin MD90-29A018, dated 
October 21, 1999. 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 Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on December 18, 2001.

    Issued in Renton, Washington, on November 1, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-28023 Filed 11-9-01; 8:45 am]
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