[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]



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

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.

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

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