[Federal Register Volume 68, Number 82 (Tuesday, April 29, 2003)]
[Proposed Rules]
[Pages 22644-22646]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-10513]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-326-AD]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model 382G 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 certain Lockheed Model 382G series 
airplanes. This proposal would require repetitive general visual 
inspections of certain bearings located in the emergency exit door for 
evidence of excessive wear; and repair of certain bearings, which would 
terminate the repetitive inspections. These actions are necessary to 
prevent failure of the latch mechanism, which could result in the 
inability to open the emergency exit door in an emergency. This action 
is intended to address the identified unsafe condition.

DATES: Comments must be received by June 13, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-326-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-326-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 
S. Cobb Drive, Marietta, Georgia 30063. This information may be 
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, Atlanta Aircraft Certification 
Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, 
Georgia.

FOR FURTHER INFORMATION CONTACT: William Herderich, Aerospace Engineer, 
Airframe and Propulsion Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 
450, Atlanta, Georgia 30349; telephone (770) 703-6082; fax (770) 703-
6097.

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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-326-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. 2000-NM-326-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA received a report from an operator that, during an 
inspection, an emergency exit door could not be opened on a Lockheed 
Model 382G series airplane. Further investigation revealed that the 
latch mechanism failed due to excessive wear of the latch bearings in 
the door. The excessive wear was caused by steel roll pins rubbing 
against aluminum bearings and creating grooves, which consequently 
inhibited the rotation of the tube that retracts the door latches. The 
same operator also reported that excessive bearing wear was found in 
nine additional airplanes. Failure of the latch mechanism, if not 
corrected, could result in the inability to open the emergency exit 
door in an emergency.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Hercules Service Bulletin 382-52-
9, dated July 5, 2000, which describes procedures for repetitive 
general visual inspections of certain bearings located in the emergency 
exit door for evidence

[[Page 22645]]

of excessive wear (demonstrated by a groove in excess of 0.060 inch 
deep); and repair of certain bearings, which would terminate the 
repetitive inspections. The repair procedures include machining the 
bearing faces so the roll pins will not contact the bearings and cause 
additional wear. Accomplishment of the actions specified in the service 
bulletin is intended to adequately address the identified unsafe 
condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletin described previously, except as discussed below.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that this proposed AD would require, within 
90 days of the effective date of this AD, repair of bearings having P/N 
3326653-1 and P/N 3326653-2, as terminating action for the repetitive 
inspections. The referenced service bulletin specifies the repair as 
optional. The FAA has determined that long-term continued operational 
safety will be better assured by removing the source of the problem, 
rather than by repetitive inspections. Long-term inspection may not be 
providing the degree of safety assurance necessary for the transport 
airplane fleet. This, coupled with a better understanding of the human 
factors associated with numerous continual inspections, has led the FAA 
to consider placing less emphasis on inspections and more emphasis on 
repairs. The proposed repair requirement is consistent with these 
conditions.

Cost Impact

    There are approximately 10 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 1 airplane of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
16 work hours to accomplish the proposed actions, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be $9,600, 
or $960 per airplane.
    The cost impact figure discussed above is 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 proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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:

Lockheed: Docket 2000-NM-326-AD.

    Applicability: Model 382G series airplanes, as listed in 
Hercules Service Bulletin 382-52-9, dated July 5, 2000, 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 failure of the latch mechanism located inside the 
emergency exit door, which could result in the inability to open the 
door in an emergency, accomplish the following:

Inspection

    (a) Within 30 days after the effective date of this AD: Perform 
a general visual inspection of bearings having part numbers (P/N) 
3326653-1 and 3326653-2, for evidence of a groove greater than 0.060 
inch deep. Perform the inspection per paragraph 2.A. of the 
Accomplishment Instructions specified in Hercules Service Bulletin 
382-52-9, dated July 5, 2000.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (1) If evidence of a groove greater than 0.060 inch deep is not 
found: Repeat the inspection at 30-day intervals until 
accomplishment of the terminating action required by paragraph (b) 
of this AD.
    (2) If evidence of a groove greater than 0.060 inch deep is 
found: Before further flight, repair the bearings per paragraph (b) 
of this AD.

Repair

    (b) Within 90 days after the effective date of this AD: Repair 
bearings having P/N 3326653-1 and P/N 3326653-2 per paragraph 2.B. 
of the Accomplishment Instructions specified in Hercules Service 
Bulletin 382-52-9, dated July 5, 2000. Accomplishment of this repair 
terminates the requirements of paragraph (a) of this AD.

Alternative Methods of Compliance

    (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, Atlanta

[[Page 22646]]

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, 
Atlanta ACO.

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

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Sec. Sec.  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.

    Issued in Renton, Washington, on April 23, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-10513 Filed 4-28-03; 8:45 am]
BILLING CODE 4910-13-P