[Federal Register: February 9, 2004 (Volume 69, Number 26)]
[Rules and Regulations]
[Page 5924-5926]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09fe04-10]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-170-AD, Amendment 39-13467; AD 2004-03-23]
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 (STC) SA2969SO
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Boeing Model 737-200 and -300 series
airplanes, that currently requires a one-time inspection to detect
cracks of the lower frames and reinforcing angles of the main deck
cargo door where the door latch fittings attach between certain
fuselage stations and water lines, and replacement of any cracked part
with a new part having the same part number. This amendment continues
to require the existing actions and corrects a reference to an
incorrect fuselage station. The actions specified by the AD are
intended to detect and correct cracking of the lower portion of the
main deck cargo door frames, which could result in sudden
depressurization, loss or opening of the main deck cargo door during
flight, and loss of control of the airplane.
DATES: Effective February 24, 2004.
The incorporation by reference of a certain publication, as listed
in the regulations, was approved previously by the Director of the
Federal Register as of May 29, 2001 (66 FR 20380, April 23, 2001).
Comments for inclusion in the Rules Docket must be received on or
before April 9, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-170-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:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-170-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 Pemco World Air Services, 100 Pemco Drive, Dothan, AL
36303. 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; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Don Buckley, Aerospace Engineer,
Airframe and Propulsion Branch, ACE-117A, FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite
450, Atlanta, Georgia 30337-2748, telephone (770) 703-6086; fax (770)
703-6097.
SUPPLEMENTARY INFORMATION: On April 12, 2001, the FAA issued AD 2001-
08-07, amendment 39-12184 (66 FR 20380, April 23, 2001), applicable to
certain Boeing Model 737-200 and -300 series airplanes, to require a
one-time inspection to detect cracks of the lower frames and
reinforcing angles of the main deck cargo door where the door latch
fittings attach between certain fuselage stations and water lines, and
replacement of any cracked part with a new part having the same part
number. That action was prompted by reports that, during the
inspections required by the existing AD, cracks were found in the
reinforcing angles of the main deck cargo door frame. The requirements
of that AD are intended to detect and correct cracking of the lower
portion of the main deck cargo door frames, which could result in
sudden depressurization, loss or opening of the main deck cargo door
during flight, and loss of control of the airplane.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, several commenters point out a
typographical error in paragraphs (a) and (b) of the AD. The first
sentence of those paragraphs state, `` * * * at the location where the
door latch fittings attach between fuselage station (FS) 361.86 and FS
298.12 * * *.'' FS 298.12 is incorrect; the correct FS is 498.12, which
is specified in the service bulletin cited in that AD (i.e., Pemco
Service Bulletin 737-52-003, Revision 2, dated September 13, 2000,
including
[[Page 5925]]
Attachment 1, dated August 10, 2000.) Because neither of the two
airplanes affected by this action are on the U.S. Register, the public
has not acted in reliance on the error. Therefore, public notice and
comment are unnecessary, because the public would have no interest in
commenting.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design that may be
registered in the United States at some time in the future, this AD is
being issued to detect and correct cracking of the lower portion of the
main deck cargo door frames, which could result in sudden
depressurization, loss or opening of the main deck cargo door during
flight, and loss of control of the airplane. This AD supersedes AD
2001-08-07 to require the existing one-time inspection to detect cracks
of the lower frames and reinforcing angles of the main deck cargo door
where the door latch fittings attach between the correct fuselage
stations and water lines, and replacement of any cracked part with a
new part having the same part number. The actions are required to be
accomplished in accordance with Pemco Service Bulletin 737-52-0037,
Revision 2, dated September 13, 2000, including Attachment 1, dated
August 10, 2000, described previously in AD 2001-08-07.
Cost Impact
None of the Model 737-200 and -300 series airplanes equipped with a
main deck cargo door installed in accordance with Supplemental Type
Certificate SA2969SO affected by this action are on the U.S. Register.
All airplanes included in the applicability of this rule currently are
operated by non-U.S. operators under foreign registry; therefore, they
are not directly affected by this AD action. However, the FAA considers
that this rule is necessary to ensure that the unsafe condition is
addressed in the event that any of these subject airplanes are imported
and placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 500 work hours
per airplane to accomplish the required inspection, at an average labor
rate of $65 per work hour. Based on these figures, the cost impact of
the inspection required by this AD on U.S. operators is estimated to be
$32,500 per airplane.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 128 work hours
per airplane to accomplish the replacement, at an average labor rate of
$65 per work hour. Required parts will cost approximately $15,521 per
airplane. Based on these figures, the cost impact of the replacement
required by this AD on U.S. operators is estimated to be $23,841 per
airplane.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, prior notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and 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.
Submit comments using the following format:
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.
For each issue, state what specific change to
the AD is being requested.
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 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 2003-NM-170-AD.'' The postcard will be date stamped
and returned to the commenter.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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
0
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
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. Section 39.13 is amended by removing amendment 39-12184 (66 FR
20380, April 23, 2001), and by adding a new airworthiness directive
(AD), amendment 39-13467 to read as follows:
2004-03-23 Boeing: Amendment 39-13467. Docket 2003-NM-170-AD.
Supersedes AD 2001-08-07, Amendment 39-12184.
Applicability: Model 737-200 and -300 series airplanes, equipped
with a main deck cargo door installed in accordance with
[[Page 5926]]
Supplemental Type Certificate (STC) SA2969SO; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct cracking of the lower portion of the main
deck cargo door frames, which could result in sudden
depressurization, loss or opening of the main deck cargo door during
flight, and loss of control of the airplane; accomplish the
following:
Actions Addressing Door Frames or Reinforcing Angles That Have Been
Replaced
(a) For airplanes on which any door frame or reinforcing angle
at the location where the door latch fittings attach between
fuselage station (FS) 361.86 and FS 498.12 and water line (WL)
202.35 and WL 213.00 has been replaced before the effective date of
this AD: Do the actions specified in paragraphs (a)(1) and (a)(2) of
this AD per the Accomplishment Instructions of Pemco Service
Bulletin 737-52-0037, Revision 2, dated September 13, 2000,
including Attachment 1, dated August 10, 2000.
(1) Within 3,000 flight cycles after accomplishment of the
replacement, do a high frequency eddy current (HFEC) inspection to
detect cracks of the replaced lower frames or replaced reinforcing
angles of the main deck cargo door, as applicable.
(i) If no crack is detected, repeat the HFEC inspection
thereafter at intervals of 1,300 flight cycles on the replaced part.
(ii) If any crack is detected, before further flight, replace
the cracked part with a new part having the same part number per the
service bulletin. Within 3,000 flight cycles after accomplishment of
the replacement, do the HFEC inspection required by paragraph (a)(1)
of this AD.
(2) Before or upon the accumulation of 7,000 total flight cycles
on any lower frame or reinforcing angle of the main deck cargo door,
replace the lower frame or reinforcing angle, as applicable, with
new parts. Within 3,000 flight cycles after accomplishment of the
replacement, do the HFEC inspection required by paragraph (a)(1) of
this AD.
Actions Addressing Door Frames or Reinforcing Angles That Have Not Been
Replaced
(b) For airplanes on which any door frame or reinforcing angle
at the location where the door latch fittings attach between FS
361.86 and FS 498.12 and WL 202.35 and WL 213.00 has not been
replaced before the effective date of this AD: Within 1,300 flight
cycles after accomplishment of the HFEC inspection required by AD
2000-17-51, amendment 39-11877, do the action specified in either
paragraph (b)(1) or (b)(2) of this AD, as applicable, per the
Accomplishment Instructions of Pemco Service Bulletin 737-52-0037,
Revision 2, dated September 13, 2000, including Attachment 1, dated
August 10, 2000.
(1) For airplanes that have accumulated less than 7,000 total
flight cycles since installation of STC SA2969SO: Do an HFEC
inspection to detect cracks of the lower frames and reinforcing
angles of the main deck cargo door where the door latch fittings
attach between FS 361.86 and FS 498.12 and WL 202.35 and WL 213.00.
(i) If no crack is detected, do the actions specified in
paragraphs (b)(1)(i)(A) and (b)(1)(i)(B) of this AD.
(A) Repeat the HFEC inspection thereafter at intervals of 1,300
flight cycles on the airplane, but not to exceed the accumulation of
7,000 total flight cycles on the airplane.
(B) Before the accumulation of 7,000 total flight cycles on the
airplane, replace the lower frame and reinforcing angle with new
parts per the service bulletin. Within 3,000 flight cycles after
accomplishment of the replacement, do the HFEC inspection required
by paragraph (a)(1) of this AD.
(ii) If any crack is detected, before further flight, replace
the cracked part with a new part having the same part number per the
service bulletin. Within 3,000 flight cycles after accomplishment of
the replacement, do the HFEC inspection required by paragraph (a)(1)
of this AD.
(2) For airplanes that have accumulated 7,000 or more total
flight cycles since installation of STC SA2969SO: Replace the lower
frames and reinforcing angles with new parts. Within 3,000 flight
cycles after accomplishment of the replacement, do the HFEC
inspection required by paragraph (a)(1) of this AD.
Alternative Methods of Compliance
(c)(1) In accordance with 14 CFR 39.19, the Manager, Atlanta
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance (AMOCs) for this AD.
(2) Alternative methods of compliance, approved previously in
accordance with AD 2000-17-51, amendment 39-11877, are approved as
alternative methods of compliance with the initial HFEC inspection
required by paragraph (a)(1) of this AD.
Incorporation by Reference
(d) The actions shall be done in accordance with Pemco Service
Bulletin 737-52-0037, Revision 2, dated September 13, 2000,
including Attachment 1, dated August 10, 2000. This incorporation by
reference was approved previously by the Director of the Federal
Register as of May 29, 2001 (66 FR 20380, April 23, 2001). Copies
may be obtained from Pemco World Air Services, 100 Pemco Drive,
Dothan, AL 36303. Copies may be inspected 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; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
Effective Date
(e) This amendment becomes effective on February 24, 2004.
Issued in Renton, Washington, on January 30, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-2575 Filed 2-6-04; 8:45 am]
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