Airworthiness Directives; McDonnell Douglas Model DC-8 Airplanes, 13092-13093 [05-5141]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 70, Number 52 (Friday, March 18, 2005)]
[Rules and Regulations]
[Pages 13092-13093]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5141]



[[Page 13092]]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19541; Directorate Identifier 2004-NM-129-AD; 
Amendment 39-14013; AD 2005-06-05]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
McDonnell Douglas Model DC-8 airplanes. This AD requires an inspection 
of the pushrod assemblies for the left and right elevator control tabs 
to determine if the pushrod assemblies are made of aluminum or steel, 
replacing any assembly made of aluminum with an assembly made of steel 
or modifying existing steel assemblies, and other specified actions. 
This AD also requires an inspection of the crank assemblies for the 
inboard and outboard geared tabs of the elevator to determine if the 
crank assemblies are made of aluminum or steel, replacing any assembly 
made of aluminum with an assembly made of steel, and other specified 
actions. This AD is prompted by an accident involving a DC-8 airplane. 
The probable cause of the accident was a loss of pitch control 
resulting from the disconnection of the pushrod for the right elevator 
control tab. The pushrod dropped down and jammed in front of the 
control tab crank, causing a large deflection of the control tab. We 
are issuing this AD to minimize the possibility of a control tab 
offset. A control tab offset could cause elevator deflection, an 
elevator airplane-nose-up condition, and reduced controllability of the 
airplane. This AD is also prompted by a report that the elevator on a 
McDonnell Douglas Model DC-8 airplane did not respond to command inputs 
from the flightcrew. We are also issuing this AD to minimize the 
possibility of crank assembly failure when the assembly is exposed to 
abnormal load conditions. Failure of a crank assembly could result in a 
jammed elevator and consequent reduced controllability of the airplane.

DATES: This AD becomes effective April 22, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of April 
22, 2005.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024).
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2004-19541; the directorate 
identifier for this docket is 2004-NM-129-AD.

FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5238; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for all McDonnell Douglas Model DC-8 airplanes. That action, 
published in the Federal Register on November 5, 2004 (69 FR 64510), 
proposed to require an inspection of the pushrod assemblies for the 
left and right elevator control tabs to determine if the pushrod 
assemblies are made of aluminum or steel, replacing any assembly made 
of aluminum with an assembly made of steel or modifying existing steel 
assemblies, and other specified actions. That action also proposed to 
require an inspection of the crank assemblies for the inboard and 
outboard geared tabs of the elevator to determine if the crank 
assemblies are made of aluminum or steel, replacing any assembly made 
of aluminum with an assembly made of steel, and other specified 
actions.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Supportive Comment

    One commenter supports the proposed AD.

Request To Revise Costs of Compliance

    One commenter requests that the Costs of Compliance section of the 
proposed AD be revised to include detailed cost information. The 
commenter states that the proposed AD requires replacement or 
modification of certain parts, therefore, the parts costs and 
associated work hours should be included in the economic analysis of 
the final rule. The commenter provides all of the parts costs and labor 
figures.
    We do not agree with the commenter's request. This AD requires 
inspections of the pushrod assemblies and inboard and outboard geared 
tab crank assemblies. The replacement or modification of certain parts 
is dependent upon the inspection results. The cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD, not the ``on 
condition'' actions. We have not changed this AD regarding this issue.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 227 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number  of
                                    Work     Average                         Cost per      U.S.-
              Action                hours   labor rate        Parts          airplane    registered   Fleet cost
                                             per hour                                    airplanes
----------------------------------------------------------------------------------------------------------------
Inspection, crank assemblies.....       1          $65  None.............          $65          170      $11,050
Inspection, pushrod assemblies...       1           65  None.............           65          170       11,050
----------------------------------------------------------------------------------------------------------------


[[Page 13093]]

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 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 have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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):

2005-06-05 McDonnell Douglas: Amendment 39-14013. Docket No. FAA-
2004-19541; Directorate Identifier 2004-NM-129-AD.

Effective Date

    (a) This AD becomes effective April 22, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all McDonnell Douglas Model DC-8 
airplanes, certificated in any category.

Unsafe Condition

    (d) This AD was prompted by an accident involving a DC-8 
airplane. The probable cause of the accident was a loss of pitch 
control resulting from the disconnection of the pushrod for the 
right elevator control tab. The pushrod dropped down and jammed in 
front of the control tab crank, causing a large deflection of the 
control tab. We are issuing this AD to minimize the possibility of a 
control tab offset. A control tab offset could cause elevator 
deflection, an elevator airplane-nose-up condition, and reduced 
controllability of the airplane. This AD was also prompted by a 
report that the elevator on a McDonnell Douglas Model DC-8 airplane 
did not respond to command inputs from the flightcrew. We are also 
issuing this AD to minimize the possibility of a crank assembly 
failure when the assembly is exposed to abnormal load conditions. 
Failure of a crank assembly could result in a jammed elevator and 
consequent reduced controllability of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspection of Pushrod Assemblies and Other Specified Actions

    (f) Within 24 months after the effective date of this AD: Do an 
inspection of the pushrod assemblies located in the left and right 
elevator control tabs to determine whether the assemblies are made 
of aluminum or steel. Replace any pushrod assembly made of aluminum 
with a new, improved pushrod assembly made of steel, or modify any 
existing steel pushrod assembly by replacing the aft end assembly 
with a new, improved aft end assembly, as applicable. Do the 
inspection, replacement or modification, and all other applicable 
specified actions by accomplishing all of the actions in the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC8-
27A281, dated June 2, 2004. The replacement or modification and 
other applicable specified actions must be done before further 
flight.

Inspection of Geared Tab Crank Assemblies and Other Specified Actions

    (g) Within 24 months after the effective date of this AD: Do an 
inspection of the inboard and outboard geared tab crank assemblies, 
located in the left and right elevators, to determine whether the 
assemblies are made of aluminum or steel. Replace any crank assembly 
made of aluminum with a new, improved crank assembly made of steel. 
Do the inspection, replacement, and other applicable specified 
actions by accomplishing all of the actions in the Accomplishment 
Instructions of Boeing Alert Service Bulletin DC8-27A280, dated June 
2, 2004. The replacement and other applicable specified actions must 
be done before further flight.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, Los Angeles Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (i) You must use Boeing Alert Service Bulletin DC8-27A280, dated 
June 2, 2004; and Boeing Alert Service Bulletin DC8-27A281, dated 
June 2, 2004; as applicable; to perform the actions that are 
required by this AD; unless the AD specifies otherwise. The Director 
of the Federal Register approves the incorporation by reference of 
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. For copies of the service information, contact Boeing Commercial 
Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). For information on the availability of this 
material at the National Archives and Records Administration (NARA), 
call (202) 741-6030, or go to https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_locations.html. You may 
view the AD docket at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, 
Nassif Building, Washington, DC.

    Issued in Renton, Washington, on March 8, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-5141 Filed 3-17-05; 8:45 am]
BILLING CODE 4910-13-P