[Federal Register Volume 60, Number 4 (Friday, January 6, 1995)]
[Rules and Regulations]
[Pages 2005-2007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-283]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-225-AD Amendment 39-9115; AD 95-01-04]
Airworthiness Directives; Boeing Model 747-100 Series Airplanes
Equipped With Freighter Conversion Modification Installed in Accordance
With Supplemental Type Certificate (STC) SA2322SO
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 747-100 series airplanes. This
action requires an inspection to detect discrepancies of the lap joint
in certain fuselage stations, repair of any discrepancies, and
modification of a certain lap joint. This amendment is prompted by
reports of holes in the lap joints and longerons of these airplanes.
The actions specified in this AD are intended to prevent reduced
fatigue life of the fuselage in the areas in which holes are found.
DATES: Effective January 23, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 23, 1995.
Comments for inclusion in the Rules Docket must be received on or
before March 7, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-225-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
GATX/Airlog Company, Tulsa International Airport, P.O. Box 582527,
Tulsa, Oklahoma 74158. This information may be examined 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.
FOR FURTHER INFORMATION CONTACT: Steven C. Fox, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (206) 227-2777; fax (206) 227-1181.
SUPPLEMENTARY INFORMATION: On July 3, 1990, the FAA issued AD 90-15-06,
amendment 39-6653 (55 FR 28600, July 12, 1990), applicable to certain
Boeing Model 747 series airplanes, to require inspection to detect
cracking and corrosion of the skin lap joints in the fuselage upper
lobe, and repair, if necessary. Recently, operators of Model 747-100
series airplanes have reported finding ``hidden'' open fastener holes
in the middle row of the lap joint, as well as misdrilled holes,
elongated holes, ``figure eight'' holes, and short-edged margins in the
fastener holes of the fuselage skin. Additionally, one operator
reported finding multiple open, misdrilled, and ``figure eight''
fastener holes in the structural longeron beneath the lap joints. These
holes were found during inspections being performed in accordance with
AD 90-15-06. In each case, these holes were found on Boeing Model 747-
100 series airplanes that had been modified by GATX/Airlog Company in
accordance with Supplemental Type Certificate (STC) SA2322SO.
Fastener holes in the lap joint and longeron of the fuselage, if
not corrected, could reduce the fatigue life of the fuselage in the
affected area.
GATX installed a main deck cargo side door on these airplanes as
part of a conversion that reconfigured these airplanes to freighters.
The modification includes installation of an external doubler over
portions of the lap joint of the fuselage skin at stringer 4L between
fuselage stations 1660 and 2040. The installation of the doubler makes
it impossible to perform the inspection required by AD 90-15-06 without
first removing the doubler to perform the inspection. The modification
also entails removal of the original lap joint hat section stringer and
replacement with a ``T'' section longeron. This longeron was designed
to carry body bending loads around the door structure.
The FAA has reviewed and approved GATX/Airlog Service Bulletin 94-
MG-1000-009, dated May 4, 1994, which describes procedures for
modification of the longitudinal lap joint in the upper body skin of
stringer 4L, at fuselage station (FS) 1689.5 to FS 1741.1, and FS
1961.1 to FS 2010.5. This modification entails removal of two sections
of the lap joints in stringer 4L. These lap joints currently are hidden
by the modification that was accomplished in accordance with STC
SA2322SO. Removal of these sections of the lap joint also constitutes
terminating action for the inspections required by AD 90-15-06 for the
lap joint section that was removed.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, this AD is
being issued to prevent reduced fatigue life of the fuselage in the
area in which holes are found. This AD requires a one-time detailed
close visual inspection of the lap joint of stringer 4L from fuselage
stations 1660 to 2040 to detect discrepancies (such as corrosion,
cracking, open holes, misdrilled holes, and any freeze plugs in the
fuselage skin and internal stringer or longerons). Any discrepancy
detected must be repaired in accordance with a method approved by the
FAA. Additionally, this AD requires that operators submit a report of
their findings, positive or negative, to the FAA.
This AD also requires modification of the longitudinal lap joint in
the upper body skin of stringer 4L at FS 1689.5 to FS 1741.1, and FS
1961.1 to FS 2010.5. The modification is required to be accomplished in
accordance with the service bulletin described previously.
Accomplishment of this modification terminates the inspections required
by AD 90-15-06 at this location only.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of [[Page 2006]] compliance with the AD, in
accordance with the paragraph of each AD that provides for such
approvals. A note has been included in this rule to clarify this
requirement.
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, 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 94-NM-225-AD.'' The postcard will be date stamped and
returned to the commenter.
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, 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-01-04 Boeing: Amendment 39-9115. Docket 94-NM-225-AD.
Applicability: Model 747-100 series airplanes equipped with
freighter conversion modification installed in accordance with
Supplemental Type Certificate (STC) SA2322SO, 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 use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent reduced fatigue life of the fuselage, accomplish the
following:
(a) Within 90 days after the effective date of this AD, perform
a detailed close visual inspection of the tee chord and lap joint of
stringer 4L from fuselage station (FS) 1660 to FS 2040 to detect
discrepancies (such as corrosion, cracking, open holes, misdrilled
holes, and any freeze plugs in the fuselage skin and internal
stringer or longerons). External structural doublers must be removed
to perform this inspection.
(1) If no discrepancy is detected, prior to further flight,
modify the longitudinal lap joints of the upper body skin at
stringer 4L at FS 1689.5 to FS 1741.1, and FS 1961.1 to FS 2010.5,
in accordance with GATX/Airlog Service Bulletin 94-MG-1000-009,
dated May 4, 1994. Accomplishment of this modification constitutes
terminating action for the inspections required by AD 90-15-06,
amendment 39-6653.
(2) If any discrepancy is detected, prior to further flight,
repair in accordance with a method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate.
(b) Within 30 days after the airplane is returned to service
subsequent to the completion of the inspection required by paragraph
(a) of this AD, submit a report of the findings of that inspection,
positive or negative, to the FAA, Transport Airplane Directorate,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056; or fax the report to (206) 227-1181.
The report must include the information contained in paragraphs
(b)(1), (b)(2), (b)(3), and (b)(4) of this AD. Information
collection requirements contained in this regulation have been
approved by the Office of Management and Budget (OMB) under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control Number 2120-0056.
(1) Serial number of the airplane;
(2) Date of completion of the modification installed in
accordance with STC SA2322S0;
(3) Date of the last inspection performed in accordance with the
requirements of AD 90-15-06, amendment 39-6653; and
(4) Description and location of each discrepancy detected during
the inspection required by paragraph (a) of this AD.
(c) As of the effective date of this AD, modification of the
longitudinal lap joints of the upper body skin at stringer 4L, FS
1689.5 to FS 1741.1, and FS 1961.1 to FS 2010.5, must be
accomplished in accordance with GATX/Airlog Service Bulletin 94-MG-
1000-009, dated May 4, 1994, prior to installation of Supplemental
Type Certificate (STC) SA2322SO on any airplane in accordance with
the STC.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
[[Page 2007]] used if approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA, Transport Airplane Directorate.
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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(e) 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.
(f) The modification shall be done in accordance with GATX/
Airlog Service Bulletin 94-MG-1000-009, dated May 4, 1994. 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 GATX/Airlog Company, Tulsa
International Airport, P.O. Box 582527, Tulsa, Oklahoma 74158.
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.
(g) This amendment becomes effective on January 23, 1995.
Issued in Renton, Washington, on December 27, 1994.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-283 Filed 1-5-95; 8:45 am]
BILLING CODE 4910-13-U
