[Federal Register Volume 63, Number 35 (Monday, February 23, 1998)]
[Rules and Regulations]
[Pages 8850-8851]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-4245]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-30-AD; Amendment 39-10352; AD 98-04-41]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-200 and -300 Series
Airplanes Equipped With a Main Deck Cargo Door Installed in Accordance
With Supplemental Type Certificate SA2969SO
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Boeing Model 737-200 and -300 series
airplanes. This action requires repetitive inspections to detect cracks
in the hinge and lift actuator box area of the main deck cargo door and
upper jamb of the fuselage; and repair or replacement of any cracked
part with a new part having the same part number. This amendment is
prompted by a report that, during a periodic heavy maintenance check,
cracks were found in the upper jamb area of the fuselage and in the
main deck cargo door. The actions specified in this AD are intended to
detect and correct such cracking, which could result in reduced
structural integrity of the main cargo door and/or fuselage, and
consequent loss or opening of the main deck cargo door while the
airplane is in flight, or reduced controllability of the airplane.
DATES: Effective March 10, 1998.
Comments for inclusion in the Rules Docket must be received on or
before April 24, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-30-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
Information concerning this amendment may be obtained from or
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Small Airplane Directorate,
Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix
Boulevard, Suite 450, Atlanta, Georgia 30349.
FOR FURTHER INFORMATION CONTACT: Curtis Jackson, Aerospace Engineer,
Airframe and Propulsion Branch, ACE-117A, FAA, Small Airplane
Directorate, Atlanta Aircraft Certification Office, One Crown Center,
1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone
(770) 703-6083; fax (770) 703-6097.
SUPPLEMENTARY INFORMATION: The FAA has received a report that, during a
periodic heavy maintenance check of a Boeing Model 737-300 series
airplane equipped with a main deck cargo door installed in accordance
with Supplemental Type Certificate SA2969SO, cracks were found in the
upper jamb area of the fuselage and in the main cargo door. The cracks
were between 0.50 inches and 2.35 inches in length. The cause of such
cracking is unknown at this time. However, several scenarios (e.g.,
improper cargo door operations during loading and unloading of cargo,
and improper fastener locations) are being examined at this time to
determine a possible cause of the cracking.
Cracking in the upper jamb area of the fuselage or in the main deck
cargo door, if not corrected, could result in reduced structural
integrity of the main deck cargo door and/or fuselage, and consequent
loss or opening of the main deck cargo door while the airplane is in
flight, or reduced controllability of the airplane.
Explanation of the Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other Boeing Model 737-200 and -300 series
airplanes, equipped with a main deck cargo door installed in accordance
with Supplemental Type Certificate SA2969SO, of the same type design,
this AD is being issued to detect and correct cracking in the upper
jamb area of the fuselage and in the main deck cargo door; such
cracking could result in reduced structural integrity of the main deck
cargo door and/or fuselage, and consequent loss or opening of the main
deck cargo door while the airplane is in flight, or reduced
controllability of the airplane. This AD requires repetitive detailed
visual inspections to detect cracks in the hinge and lift actuator box
area of the main deck cargo door and upper jamb of the fuselage; and
replacement of any cracked part with a new part having the same part
number, or repair in accordance with a method approved by the FAA.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments,
[[Page 8851]]
in the Rules Docket for examination by interested persons. A report
that summarizes each FAA-public contact concerned with the substance of
this AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-30-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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, 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:
98-04-41 Boeing: Amendment 39-10352. Docket 98-NM-30-AD.
Applicability: Model 737-200 and -300 series airplanes equipped
with a main deck cargo door installed in accordance with
Supplemental Type Certificate (STC) SA2969SO; certificated in any
category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 detect and correct cracking in the upper jamb area of the
fuselage and in the main cargo door, which could result in reduced
structural integrity of the main cargo door and/or fuselage, and
consequent loss or opening of the main cargo door while the airplane
is in flight, or reduced controllability of the airplane, accomplish
the following:
(a) Within 10 days after the effective date of this AD, and
thereafter at intevals not to exceed 600 flight cycles, perform a
detailed visual inspection to detect cracks in the hinge and lift
actuator box area of the main deck cargo door and upper jamb of the
fuselage. Pay particular attention to the upper frame of the
fuselage and upper jamb frames of the main deck cargo door, primary
longeron, and clips of the fuselage, primarily in the hinge and lift
actuator box area. If any crack is detected, prior to further
flight, replace the cracked part with a new part having the same
part number, or repair in accordance with a method approved by the
Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small
Airplane Directorate.
(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, Atlanta ACO. 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(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.
(d) This amendment becomes effective on March 10, 1998.
Issued in Renton, Washington, on February 12, 1998.
Gilbert L. Thompson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-4245 Filed 2-20-98; 8:45 am]
BILLING CODE 4910-13-U
