[Federal Register: August 27, 2003 (Volume 68, Number 166)]
[Proposed Rules]
[Page 51521-51523]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27au03-26]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-180-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and
747SP 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 Boeing airplane models.
This proposal would require a one-time inspection to identify all H-11
steel bolts installed in the latch fittings of the cargo doors,
repetitive inspections for cracked or broken H-11 steel bolts, and
follow-on and corrective actions if necessary. This proposal also would
require eventual replacement of all H-11 steel bolts in the latch
fittings of the cargo doors with Inconel bolts. This action is
necessary to prevent broken bolts in the latch fittings, which could
reduce the capability of the door latch to keep the door closed, and
result in loss of a cargo door and consequent rapid depressurization of
the airplane. This action is intended to address the identified unsafe
condition.
DATES: Comments must be received by October 14, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-180-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. 2001-NM-180-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 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Rick Kawaguchi, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6434; fax (425) 917-6590.
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 2001-NM-180-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. 2001-NM-180-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report of five corroded and broken bolts
common to two of the latch fittings for the main deck side cargo door
on a Boeing Model 747-300 series airplane. The affected bolts are made
from H-11 steel, a material that is susceptible to corrosion and
subsequent stress corrosion cracking. Broken H-11 steel bolts in the
latch fittings of the cargo door could reduce the capability of the
door latch to keep the door closed. This condition, if not corrected,
could result in loss of the cargo door and consequent rapid
depressurization of the airplane.
The same H-11 steel bolts used in the latch fittings of the main
deck side cargo door of Boeing Model 747-300 series airplanes are also
used in the latch fittings of the main deck side cargo door, nose cargo
door, and the forward and aft lower lobe cargo doors on certain Boeing
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F,
747-400, 747SR, and 747SP series airplanes. Therefore, the subject
doors on all of these airplane models may be subject to the same unsafe
condition.
Explanation of Relevant Service Information
We have reviewed and approved Boeing Alert Service Bulletin 747-
53A2464, Revision 1, dated August 30, 2001. That service bulletin
describes procedures for a one-time inspection to identify all H-11
steel bolts installed in the latch fittings of the main deck side cargo
door, nose cargo door, and the forward and aft lower lobe cargo doors.
The inspection procedures include
[[Page 51522]]
checking the bolt part number, which is stamped on the bolt head; or
using a magnet to verify that the bolt is made of steel. The service
bulletin also describes procedures for repetitive ultrasonic
inspections for cracked or broken H-11 steel bolts, and replacement of
H-11 steel bolts with Inconel bolts. The procedures for replacement of
H-11 steel bolts involve performing a detailed inspection of the bolt
hole for corrosion; oversizing the bolt hole to remove any corrosion;
installing a new bolt, nut, and washers; and applying sealant.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
Other Relevant Rulemaking
Boeing Alert Service Bulletin 747-53A2464, Revision 1, specifies
that the actions in Boeing Alert Service Bulletin 747-52A2167 must have
been accomplished previously or must be accomplished concurrently. The
FAA has previously issued AD 80-14-11, amendment 39-3831. That AD
applies to all Model 747 series airplanes equipped with nose cargo
doors, and requires, before further flight (as of July 15, 1980, the
effective date of that AD), an inspection for loose or missing bolts of
the portal latch fittings of the nose cargo door, and corrective
actions if necessary, per Boeing Alert Service Bulletin 747-52A2167,
Revision 1, dated March 28, 1980. Because the initial compliance time
of AD 80-14-11 has long passed, this AD does not specify a requirement
for accomplishing that service bulletin.
Explanation of Requirements of Proposed AD
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
Boeing Alert Service Bulletin 747-53A2464, Revision 1, except as
discussed below. The actions would be required to be accomplished in
accordance with the service bulletin described previously.
Differences Between This Proposed AD and Boeing Alert Service Bulletin
747-53A2464, Revision 1
The service bulletin does not specify the type of inspection
necessary to identify H-11 steel bolts or to find corrosion during
accomplishment of the replacement of H-11 bolts with improved bolts.
For the purposes of this proposed AD, we have determined that the
procedures in the service bulletin constitute a ``detailed
inspection.'' Note 1 of this proposed AD defines such an inspection.
Although the service bulletin specifies that the manufacturer may
be contacted for disposition of certain repairs, this proposed AD would
require such repairs to be accomplished per a method approved by the
FAA, or per data meeting the type certification basis of the airplane
approved by a Boeing Company Designated Engineering Representative who
has been authorized by the Manager, Seattle Aircraft Certification
Office, to make such findings.
The service bulletin specifies that the actions therein should be
accomplished prior to or concurrently with the actions in Boeing
Service Bulletin 747-52-2197. We have determined that it is not
necessary at this time to require accomplishment of Boeing Service
Bulletin 747-52-2197. This determination is based on our decision that
the inspection of the portal latch fitting of the nose cargo door
described in that service bulletin does not address an immediate safety
issue. Service history shows that there have been no significant
adverse findings since the issuance of that service bulletin; thus, the
subject of that service bulletin is not an area of concern.
Changes to 14 CFR Part 39/Effect on the Proposed AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOCs). Because we have now included this material in part
39, only the office authorized to approve AMOCs is identified in this
proposed AD.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
There are approximately 566 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 179 airplanes of U.S. registry
would be affected by this proposed AD, that it would take between 2 and
8 work hours per airplane (depending on the airplane's configuration)
to accomplish the proposed inspection, and that the average labor rate
is $65 per work hour. Based on these figures, the cost impact of the
proposed AD on U.S. operators is estimated to be between $130 and $520
per airplane.
The cost impact figures discussed above are 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:
[[Page 51523]]
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:
Boeing: Docket 2001-NM-180-AD.
Applicability: Model 747-100, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP series
airplanes; line numbers 1 through 721 inclusive, 976, and 982;
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent bolts from breaking in the latch fittings of the
cargo doors, which could reduce the capability of the door latch to
keep the door closed, and result in loss of a cargo door and
consequent rapid depressurization of the airplane, accomplish the
following:
Service Bulletin References
(a) The following information pertains to the service bulletin
referenced in this AD:
(1) The term ``service bulletin'' as used in this AD, means the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2464, Revision 1, dated August 30, 2001.
(2) Although the service bulletin referenced in this AD
specifies to submit certain information to the manufacturer, this AD
does not include such a requirement.
(3) Although the service bulletin specifies that the actions
therein must be accomplished prior to or concurrently with the
actions in Boeing Alert Service Bulletin 747-52A2167 and Boeing
Service Bulletin 747-52-2197, this AD does not include such a
requirement. AD 80-14-11, amendment 39-3831, already requires
accomplishment of Boeing Alert Service Bulletin 747-52A2167,
Revision 1, dated March 28, 1980.
(4) Inspections and replacements accomplished before the
effective date of this AD per Boeing Alert Service Bulletin 747-
53A2464, dated March 15, 2001, are considered acceptable for
compliance with this AD.
Initial Inspection
(b) Within 1 year after the effective date of this AD: Do a one-
time detailed inspection to identify all H-11 steel bolts installed
in the latch fittings of the main deck side cargo door, nose cargo
door, and the forward and aft lower lobe cargo doors, as applicable.
Do the inspection by checking the bolt part number stamped on the
bolt head, or verifying the bolt is steel by using a magnet, per the
service bulletin. If no H-11 steel bolt is found, no further action
is required by this paragraph. If any H-11 steel bolt is found, do
the requirements of paragraph (c) of this AD.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Follow-On Inspections/Corrective Actions
(c) For any H-11 steel bolt found during any inspection required
by paragraph (b) of this AD: Before further flight, do an ultrasonic
inspection for cracked or broken bolts, or replace the H-11 steel
bolt with an Inconel bolt, per the service bulletin. Replace any
cracked or broken bolt with an Inconel bolt before further flight
per the service bulletin. Repeat the ultrasonic inspection of
remaining H-11 steel bolts in the latch fittings of the main deck
side cargo door, nose cargo door, and the forward and aft lower lobe
cargo doors, at intervals not to exceed 18 months until the
terminating action required by paragraph (d) of this AD is done.
Terminating Action
(d) Within 6 years after the effective date of this AD: Replace,
with Inconel bolts, all H-11 steel bolts in the latch fittings of
the main deck side cargo door, nose cargo door, and the forward and
aft lower lobe cargo doors, per the service bulletin. The procedures
for this replacement include performing a detailed inspection of the
bolt hole for corrosion; oversizing the bolt hole to remove any
corrosion; installing a new bolt, nut, and washers; and applying
sealant. Such replacement terminates the repetitive inspections
required by paragraph (c) of this AD. If corrosion is found and
oversizing the bolt hole within the limits specified in the service
bulletin is not adequate to remove the corrosion, before further
flight, repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or per data
meeting the type certification basis of the airplane approved by a
Boeing Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make such findings. For a
repair method to be approved, the approval must specifically
reference this AD.
Parts Installation
(e) As of the effective date of this AD: No person may install,
on any airplane, an H-11 steel bolt in the latch fittings of the
main deck side cargo door, nose cargo door, or the forward and aft
lower lobe cargo doors.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the Manager, Seattle ACO,
is authorized to approve alternative methods of compliance for this
AD.
Issued in Renton, Washington, on August 20, 2003.
Kyle L. Olsen,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-21873 Filed 8-26-03; 8:45 am]
BILLING CODE 4910-13-P